:::::::::::::: 7037EF1.LFT :::::::::::::: Airfoil: SD7037 (E) Builder: J. Robertson Comment: clean, LE flap = -3 degs, TE flap = -2.5 degs Number of Reynolds #'s: 3 Average Reynolds #: 99967 Number of angles of attack: 59 alpha / Cl / Cm -9.14 -0.587 0.0467 -8.10 -0.574 0.0290 -7.16 -0.528 -0.0171 -5.97 -0.423 -0.0498 -5.17 -0.359 -0.0482 -4.13 -0.280 -0.0437 -3.10 -0.207 -0.0391 -2.10 -0.117 -0.0384 -1.07 0.010 -0.0439 -0.04 0.187 -0.0550 0.97 0.323 -0.0566 2.04 0.423 -0.0508 3.12 0.515 -0.0432 4.14 0.607 -0.0374 5.12 0.692 -0.0314 6.31 0.798 -0.0234 7.16 0.867 -0.0192 8.21 0.939 -0.0143 9.24 0.997 -0.0086 10.22 1.070 -0.0027 11.26 1.101 0.0016 12.10 1.014 -0.0891 13.17 0.917 -0.1051 14.13 0.897 -0.1055 15.30 0.919 -0.1082 16.09 0.954 -0.1150 17.16 0.931 -0.1125 18.09 0.948 -0.1217 19.04 0.933 -0.1297 20.13 0.980 -0.1265 19.58 0.972 -0.1306 18.58 0.978 -0.1291 17.62 0.937 -0.1263 16.59 0.943 -0.1164 15.59 0.940 -0.1140 14.59 0.901 -0.1067 13.56 0.893 -0.1087 12.59 0.903 -0.0980 11.74 1.112 -0.0060 10.70 1.089 -0.0007 9.65 1.024 -0.0049 8.73 0.984 -0.0092 7.73 0.921 -0.0144 6.67 0.843 -0.0200 5.61 0.754 -0.0258 4.62 0.666 -0.0318 3.54 0.571 -0.0396 2.57 0.486 -0.0451 1.48 0.381 -0.0514 0.54 0.281 -0.0543 -0.54 0.118 -0.0458 -1.55 -0.044 -0.0340 -2.60 -0.155 -0.0315 -3.74 -0.243 -0.0335 -4.65 -0.314 -0.0381 -5.64 -0.390 -0.0415 -6.68 -0.499 -0.0300 -7.64 -0.557 0.0194 -8.64 -0.557 0.0355 Tabulated from data in file cl02316.dat & reduced using program C06.01 Average Reynolds #: 200046 Number of angles of attack: 59 alpha / Cl / Cm -9.12 -0.577 0.0413 -8.19 -0.595 0.0245 -7.18 -0.550 -0.0121 -6.05 -0.434 -0.0551 -5.11 -0.360 -0.0515 -4.12 -0.280 -0.0471 -3.14 -0.153 -0.0527 -2.04 -0.004 -0.0574 -1.04 0.099 -0.0547 0.25 0.224 -0.0494 0.96 0.295 -0.0457 2.02 0.396 -0.0421 3.03 0.506 -0.0388 4.08 0.612 -0.0345 5.14 0.718 -0.0297 6.17 0.811 -0.0239 7.21 0.898 -0.0181 8.25 0.983 -0.0132 9.29 1.056 -0.0073 10.23 1.116 -0.0023 11.25 1.165 0.0030 12.26 1.193 0.0076 13.25 1.196 0.0055 14.21 0.975 -0.1082 15.16 0.991 -0.1170 16.20 1.035 -0.1199 17.14 1.026 -0.1191 18.16 1.026 -0.1211 19.23 0.948 -0.1422 20.19 0.989 -0.1373 19.62 0.952 -0.1286 18.62 0.905 -0.1336 17.62 1.033 -0.1239 16.49 1.019 -0.1179 15.62 1.017 -0.1168 14.50 1.008 -0.1131 13.49 0.987 -0.1094 12.49 1.042 -0.0995 11.78 1.182 0.0075 10.78 1.143 0.0026 9.59 1.076 -0.0040 8.75 1.019 -0.0090 7.69 0.940 -0.0143 6.68 0.854 -0.0192 5.66 0.768 -0.0245 4.59 0.663 -0.0293 3.57 0.561 -0.0338 2.53 0.458 -0.0374 1.55 0.345 -0.0393 0.50 0.243 -0.0450 -0.55 0.143 -0.0507 -1.87 0.007 -0.0538 -2.78 -0.100 -0.0525 -3.60 -0.219 -0.0453 -4.65 -0.321 -0.0447 -5.79 -0.411 -0.0505 -6.72 -0.506 -0.0350 -7.70 -0.565 0.0048 -8.63 -0.608 0.0325 Tabulated from data in file cl02314.dat & reduced using program C06.01 Average Reynolds #: 300106 Number of angles of attack: 59 alpha / Cl / Cm -9.03 -0.621 0.0369 -8.21 -0.607 0.0191 -7.09 -0.546 -0.0281 -5.89 -0.420 -0.0553 -4.97 -0.343 -0.0513 -3.83 -0.206 -0.0550 -2.74 -0.069 -0.0591 -1.81 0.025 -0.0560 -0.44 0.162 -0.0498 0.17 0.225 -0.0478 1.13 0.325 -0.0439 2.04 0.415 -0.0401 3.15 0.533 -0.0355 4.09 0.631 -0.0323 5.10 0.729 -0.0273 6.12 0.824 -0.0233 7.33 0.934 -0.0176 8.27 1.020 -0.0134 9.23 1.094 -0.0084 10.25 1.160 -0.0025 11.28 1.208 0.0037 12.36 1.240 0.0082 13.28 1.246 0.0060 13.54 1.042 -0.1043 15.15 1.034 -0.1135 16.26 1.056 -0.1186 17.51 1.107 -0.1173 18.19 1.089 -0.1237 19.29 1.118 -0.1271 20.12 1.139 -0.1299 19.44 1.121 -0.1269 18.61 1.092 -0.1298 17.69 1.114 -0.1261 16.64 1.044 -0.1177 15.63 1.042 -0.1144 14.59 1.008 -0.1122 13.64 1.027 -0.1025 12.77 1.164 -0.0809 11.81 1.229 0.0095 10.78 1.184 0.0045 9.72 1.123 -0.0020 8.75 1.053 -0.0077 7.65 0.959 -0.0130 6.63 0.865 -0.0179 5.60 0.776 -0.0235 4.59 0.678 -0.0286 3.56 0.573 -0.0332 2.58 0.471 -0.0365 1.50 0.358 -0.0414 0.21 0.224 -0.0462 -1.22 0.080 -0.0516 -1.90 0.014 -0.0546 -2.73 -0.071 -0.0569 -3.73 -0.197 -0.0529 -4.63 -0.310 -0.0491 -5.75 -0.413 -0.0533 -6.72 -0.503 -0.0424 -7.65 -0.576 -0.0037 -8.59 -0.620 0.0265 Tabulated from data in file cl02312.dat & reduced using program C06.01 File 7037ef1.lft created using program C06.01 on Mon Feb 02 15:11:35 1998 :::::::::::::: 7037EF2.LFT :::::::::::::: Airfoil: SD7037 (E) Builder: J. Robertson Comment: clean, LE flap = 0 degs, TE flap = 0 degs Number of Reynolds #'s: 3 Average Reynolds #: 99885 Number of angles of attack: 59 alpha / Cl / Cm -9.10 -0.425 0.0286 -8.06 -0.409 0.0165 -7.14 -0.409 -0.0038 -6.14 -0.359 -0.0378 -5.14 -0.254 -0.0646 -4.14 -0.175 -0.0637 -3.11 -0.090 -0.0637 -2.08 0.009 -0.0669 -1.07 0.118 -0.0670 -0.01 0.307 -0.0795 1.10 0.463 -0.0845 2.02 0.548 -0.0812 3.05 0.631 -0.0715 4.12 0.724 -0.0641 5.13 0.821 -0.0581 6.14 0.924 -0.0525 7.18 1.018 -0.0475 8.19 1.092 -0.0415 9.21 1.165 -0.0357 10.26 1.208 -0.0289 11.30 1.244 -0.0233 12.24 1.272 -0.0196 13.27 1.278 -0.0158 14.23 1.009 -0.1219 15.17 1.002 -0.1323 16.06 0.996 -0.1281 17.13 1.018 -0.1410 18.11 0.993 -0.1314 19.22 1.046 -0.1489 20.13 1.060 -0.1522 19.62 1.076 -0.1607 18.50 1.030 -0.1485 17.59 0.994 -0.1391 16.60 1.004 -0.1440 15.64 0.987 -0.1359 14.60 1.037 -0.1358 13.58 0.987 -0.1331 12.79 1.279 -0.0242 11.80 1.261 -0.0193 10.67 1.218 -0.0245 9.75 1.183 -0.0303 8.64 1.118 -0.0375 7.71 1.052 -0.0410 6.68 0.971 -0.0468 5.68 0.878 -0.0510 4.57 0.772 -0.0584 3.60 0.675 -0.0640 2.54 0.584 -0.0735 1.49 0.491 -0.0825 0.52 0.378 -0.0814 -0.52 0.219 -0.0698 -1.57 0.063 -0.0604 -2.59 -0.041 -0.0568 -3.60 -0.133 -0.0545 -4.64 -0.218 -0.0555 -5.68 -0.321 -0.0471 -6.63 -0.408 -0.0106 -7.60 -0.427 0.0135 -8.70 -0.425 0.0266 Tabulated from data in file cl02306.dat & reduced using program C06.01 Average Reynolds #: 199915 Number of angles of attack: 59 alpha / Cl / Cm -9.11 -0.498 0.0313 -8.11 -0.483 0.0158 -7.11 -0.455 -0.0142 -6.16 -0.393 -0.0416 -5.15 -0.238 -0.0777 -4.14 -0.112 -0.0816 -3.10 0.012 -0.0862 -2.08 0.131 -0.0891 -0.93 0.248 -0.0849 -0.02 0.336 -0.0783 0.98 0.447 -0.0750 2.02 0.547 -0.0709 3.08 0.650 -0.0659 4.15 0.750 -0.0609 5.14 0.844 -0.0562 6.21 0.946 -0.0508 7.19 1.031 -0.0456 8.24 1.120 -0.0400 9.26 1.195 -0.0339 10.24 1.242 -0.0266 11.30 1.283 -0.0187 12.30 1.308 -0.0127 13.25 1.314 -0.0128 14.27 1.307 -0.0200 15.15 1.053 -0.1385 16.09 1.076 -0.1372 17.22 1.016 -0.1420 18.39 1.022 -0.1473 19.29 1.025 -0.1507 20.29 1.063 -0.1615 19.53 1.012 -0.1527 18.42 1.003 -0.1463 17.62 1.012 -0.1443 16.63 1.011 -0.1434 15.67 1.037 -0.1391 14.60 1.033 -0.1370 13.55 1.072 -0.1260 12.81 1.304 -0.0122 11.76 1.294 -0.0149 10.70 1.256 -0.0219 9.77 1.219 -0.0292 8.69 1.151 -0.0367 7.73 1.075 -0.0414 6.66 0.984 -0.0471 5.51 0.880 -0.0526 4.61 0.794 -0.0563 3.60 0.696 -0.0606 2.56 0.598 -0.0652 1.54 0.494 -0.0699 0.49 0.382 -0.0732 -0.60 0.275 -0.0786 -1.76 0.163 -0.0858 -2.65 0.062 -0.0841 -3.71 -0.064 -0.0813 -4.68 -0.184 -0.0772 -5.71 -0.323 -0.0653 -6.73 -0.439 -0.0168 -7.59 -0.470 0.0084 -8.66 -0.494 0.0224 Tabulated from data in file cl02308.dat & reduced using program C06.01 Average Reynolds #: 300044 Number of angles of attack: 59 alpha / Cl / Cm -9.07 -0.512 0.0272 -8.16 -0.489 0.0114 -7.15 -0.465 -0.0170 -6.04 -0.319 -0.0738 -4.94 -0.168 -0.0884 -4.08 -0.073 -0.0888 -2.93 0.050 -0.0883 -1.92 0.152 -0.0853 -0.94 0.248 -0.0805 0.29 0.371 -0.0738 1.30 0.480 -0.0702 2.26 0.579 -0.0669 3.13 0.667 -0.0636 4.19 0.772 -0.0596 5.11 0.861 -0.0560 6.34 0.976 -0.0504 7.21 1.055 -0.0460 8.25 1.143 -0.0404 9.24 1.217 -0.0344 10.26 1.271 -0.0274 11.31 1.317 -0.0191 12.30 1.336 -0.0135 13.30 1.342 -0.0148 14.28 1.339 -0.0240 15.28 1.328 -0.0390 16.15 1.136 -0.1373 17.13 1.117 -0.1394 18.16 1.132 -0.1490 19.14 1.163 -0.1469 20.22 1.174 -0.1499 19.71 1.185 -0.1497 18.68 1.192 -0.1434 17.59 1.153 -0.1395 16.61 1.127 -0.1390 15.55 1.101 -0.1357 14.62 1.118 -0.1310 14.37 1.339 -0.0244 12.79 1.341 -0.0093 11.75 1.329 -0.0126 10.72 1.290 -0.0192 9.73 1.242 -0.0263 8.72 1.178 -0.0333 7.79 1.105 -0.0389 6.67 1.003 -0.0453 5.65 0.909 -0.0501 4.40 0.790 -0.0561 3.58 0.708 -0.0597 2.45 0.593 -0.0643 1.44 0.488 -0.0683 0.49 0.390 -0.0720 -0.59 0.279 -0.0771 -1.56 0.182 -0.0821 -2.58 0.081 -0.0849 -3.70 -0.037 -0.0861 -4.60 -0.136 -0.0855 -5.61 -0.257 -0.0818 -6.63 -0.416 -0.0402 -7.59 -0.488 -0.0037 -8.70 -0.502 0.0214 Tabulated from data in file cl02310.dat & reduced using program C06.01 File 7037ef2.lft created using program C06.01 on Mon Feb 02 15:11:35 1998 :::::::::::::: 7037EF3.LFT :::::::::::::: Airfoil: SD7037 (E) Builder: J. Robertson Comment: clean, LE flap = 2.5 degs, TE flap = 2.5 degs Number of Reynolds #'s: 3 Average Reynolds #: 99912 Number of angles of attack: 59 alpha / Cl / Cm -9.12 -0.418 0.0141 -8.14 -0.415 0.0148 -7.11 -0.448 0.0078 -6.15 -0.388 -0.0107 -5.15 -0.218 -0.0711 -4.08 -0.073 -0.0893 -3.08 0.042 -0.0920 -2.03 0.165 -0.0972 -0.94 0.294 -0.1007 -0.04 0.418 -0.1062 1.12 0.569 -0.1063 2.00 0.658 -0.1005 3.09 0.763 -0.0941 4.10 0.851 -0.0888 5.12 0.928 -0.0825 6.12 1.004 -0.0767 7.15 1.084 -0.0726 8.22 1.178 -0.0676 9.22 1.258 -0.0630 10.33 1.323 -0.0581 11.29 1.364 -0.0523 12.28 1.381 -0.0424 13.35 1.398 -0.0384 14.27 1.394 -0.0326 15.20 1.048 -0.1438 16.09 1.062 -0.1538 17.09 1.031 -0.1525 18.11 1.042 -0.1617 19.10 1.079 -0.1715 20.13 1.071 -0.1669 19.38 1.090 -0.1740 18.52 1.058 -0.1684 17.60 1.085 -0.1575 16.55 1.072 -0.1562 15.61 1.049 -0.1583 14.62 1.049 -0.1550 13.61 1.115 -0.1521 12.81 1.384 -0.0492 11.78 1.368 -0.0472 10.60 1.340 -0.0548 9.73 1.294 -0.0589 8.71 1.218 -0.0637 7.69 1.133 -0.0683 6.66 1.049 -0.0729 5.56 0.957 -0.0782 4.40 0.864 -0.0835 3.62 0.801 -0.0886 2.48 0.696 -0.0967 1.50 0.608 -0.1045 0.48 0.492 -0.1059 -0.54 0.344 -0.1007 -1.56 0.222 -0.0980 -2.55 0.095 -0.0896 -3.68 -0.026 -0.0860 -4.66 -0.147 -0.0798 -5.63 -0.315 -0.0384 -6.62 -0.431 -0.0029 -7.68 -0.424 0.0143 -8.61 -0.393 0.0150 Tabulated from data in file cl02324.dat & reduced using program C06.01 Average Reynolds #: 199957 Number of angles of attack: 59 alpha / Cl / Cm -9.01 -0.371 0.0102 -8.11 -0.362 -0.0031 -6.99 -0.277 -0.0365 -6.15 -0.181 -0.0849 -4.88 0.001 -0.1193 -4.04 0.088 -0.1200 -2.94 0.197 -0.1192 -1.92 0.312 -0.1191 -0.80 0.411 -0.1094 0.16 0.502 -0.1023 1.01 0.601 -0.1013 2.13 0.704 -0.0967 3.05 0.792 -0.0921 4.09 0.887 -0.0871 5.13 0.982 -0.0821 6.19 1.074 -0.0765 7.17 1.160 -0.0717 8.25 1.250 -0.0661 9.26 1.328 -0.0605 10.30 1.379 -0.0520 11.23 1.398 -0.0424 12.32 1.412 -0.0355 13.31 1.416 -0.0324 14.29 1.404 -0.0394 15.29 1.387 -0.0504 16.07 1.053 -0.1555 17.37 1.116 -0.1605 18.53 1.096 -0.1674 19.39 1.124 -0.1770 20.15 1.142 -0.1779 19.33 1.096 -0.1722 18.35 1.051 -0.1681 17.63 1.126 -0.1626 16.60 1.092 -0.1624 15.65 1.066 -0.1596 14.51 1.081 -0.1555 14.05 1.402 -0.0371 12.79 1.416 -0.0322 11.79 1.404 -0.0371 10.70 1.390 -0.0470 9.72 1.358 -0.0570 8.59 1.277 -0.0635 7.70 1.203 -0.0681 6.65 1.112 -0.0730 5.55 1.012 -0.0783 4.49 0.921 -0.0834 3.65 0.842 -0.0868 2.60 0.749 -0.0919 1.49 0.639 -0.0977 0.51 0.535 -0.1002 -0.48 0.437 -0.1040 -1.67 0.333 -0.1148 -2.74 0.216 -0.1153 -3.60 0.124 -0.1150 -4.74 0.010 -0.1168 -5.64 -0.107 -0.1064 -6.58 -0.248 -0.0589 -7.93 -0.346 -0.0065 -8.62 -0.375 0.0053 Tabulated from data in file cl02326.dat & reduced using program C06.01 Average Reynolds #: 299914 Number of angles of attack: 59 alpha / Cl / Cm -9.10 -0.403 0.0082 -8.08 -0.373 -0.0092 -6.90 -0.287 -0.0525 -6.15 -0.185 -0.0903 -5.02 -0.023 -0.1177 -3.97 0.091 -0.1175 -2.87 0.205 -0.1152 -2.03 0.292 -0.1130 -0.97 0.397 -0.1084 0.12 0.504 -0.1027 1.19 0.616 -0.0992 2.49 0.744 -0.0938 3.43 0.839 -0.0904 4.38 0.925 -0.0864 5.32 1.012 -0.0819 6.24 1.096 -0.0778 7.39 1.201 -0.0724 8.28 1.278 -0.0681 9.32 1.356 -0.0609 10.33 1.395 -0.0510 11.25 1.419 -0.0418 12.27 1.434 -0.0346 13.30 1.440 -0.0350 14.28 1.433 -0.0412 15.24 1.423 -0.0517 15.65 1.097 -0.1629 17.14 1.108 -0.1607 18.04 1.078 -0.1671 19.10 1.117 -0.1776 20.10 1.143 -0.1770 19.64 1.118 -0.1768 18.58 1.085 -0.1742 17.59 1.050 -0.1655 16.58 1.068 -0.1631 15.74 1.123 -0.1644 15.39 1.423 -0.0543 13.68 1.443 -0.0358 12.79 1.421 -0.0360 11.80 1.402 -0.0422 10.80 1.402 -0.0454 9.74 1.375 -0.0539 8.56 1.303 -0.0617 7.78 1.233 -0.0654 6.66 1.132 -0.0711 5.69 1.041 -0.0756 4.65 0.949 -0.0809 3.63 0.853 -0.0857 2.56 0.753 -0.0906 1.42 0.639 -0.0959 0.39 0.535 -0.1007 -0.73 0.420 -0.1060 -1.61 0.327 -0.1081 -2.78 0.212 -0.1140 -3.59 0.129 -0.1159 -4.61 0.022 -0.1161 -5.64 -0.110 -0.1088 -6.67 -0.255 -0.0666 -7.59 -0.345 -0.0280 -8.62 -0.395 -0.0008 Tabulated from data in file cl02328.dat & reduced using program C06.01 File 7037ef3.lft created using program C06.01 on Mon Feb 02 15:11:35 1998 :::::::::::::: 7037EF4.LFT :::::::::::::: Airfoil: SD7037 (E) Builder: J. Robertson Comment: clean, LE flap = 0 degs, TE flap = 5 degs Number of Reynolds #'s: 3 Average Reynolds #: 99904 Number of angles of attack: 59 alpha / Cl / Cm -9.11 -0.376 -0.0177 -8.12 -0.317 -0.0424 -6.85 -0.153 -0.1095 -5.91 -0.046 -0.1206 -5.14 0.026 -0.1200 -4.09 0.099 -0.1159 -3.01 0.186 -0.1136 -1.98 0.254 -0.1080 -1.03 0.335 -0.1054 0.15 0.470 -0.1126 1.15 0.660 -0.1224 2.11 0.780 -0.1204 3.15 0.881 -0.1131 4.33 0.971 -0.1032 5.17 1.040 -0.0948 6.27 1.124 -0.0882 7.23 1.188 -0.0816 8.37 1.242 -0.0723 9.26 1.280 -0.0632 10.38 1.321 -0.0539 11.28 1.340 -0.0476 12.56 1.348 -0.0419 13.06 1.022 -0.1548 14.24 1.049 -0.1691 15.18 1.047 -0.1649 16.37 1.035 -0.1729 17.13 1.106 -0.1745 18.19 1.071 -0.1739 19.18 1.080 -0.1945 20.21 1.189 -0.1839 19.55 1.111 -0.1797 18.62 1.163 -0.1868 17.43 1.057 -0.1658 16.59 1.084 -0.1747 15.59 1.044 -0.1710 14.54 1.069 -0.1742 13.48 1.045 -0.1641 12.55 1.046 -0.1556 11.79 1.364 -0.0526 10.73 1.339 -0.0546 9.71 1.310 -0.0625 8.70 1.274 -0.0719 7.70 1.227 -0.0803 6.62 1.163 -0.0876 5.56 1.089 -0.0945 4.67 1.018 -0.1003 3.55 0.942 -0.1121 2.58 0.851 -0.1222 1.56 0.718 -0.1249 0.46 0.552 -0.1202 -0.49 0.425 -0.1094 -1.68 0.298 -0.1056 -2.54 0.246 -0.1137 -3.69 0.160 -0.1181 -4.71 0.068 -0.1194 -5.75 -0.026 -0.1214 -6.78 -0.135 -0.1157 -7.74 -0.280 -0.0598 -8.75 -0.362 -0.0340 Tabulated from data in file ag02367.dat & reduced using program C06.01 Average Reynolds #: 199869 Number of angles of attack: 59 alpha / Cl / Cm -9.12 -0.316 -0.0266 -8.11 -0.263 -0.0530 -7.06 -0.125 -0.1146 -5.75 0.036 -0.1319 -4.90 0.125 -0.1324 -3.63 0.259 -0.1347 -2.47 0.370 -0.1334 -1.79 0.415 -0.1296 -0.93 0.520 -0.1304 0.15 0.639 -0.1257 1.14 0.738 -0.1167 2.24 0.846 -0.1104 3.23 0.931 -0.1038 4.27 1.020 -0.0973 5.30 1.106 -0.0906 6.24 1.180 -0.0842 7.37 1.261 -0.0760 8.25 1.310 -0.0683 9.32 1.347 -0.0572 10.30 1.373 -0.0486 11.32 1.396 -0.0406 12.34 1.402 -0.0371 13.39 1.397 -0.0421 13.82 1.086 -0.1652 15.43 1.061 -0.1692 16.26 1.082 -0.1664 17.33 1.067 -0.1667 18.27 1.077 -0.1770 19.29 1.100 -0.1867 20.27 1.140 -0.1935 19.33 1.158 -0.1841 18.48 1.096 -0.1900 17.51 1.046 -0.1714 16.35 1.060 -0.1735 15.65 1.068 -0.1664 14.57 1.103 -0.1691 13.40 1.077 -0.1601 13.02 1.397 -0.0408 11.74 1.404 -0.0379 10.78 1.389 -0.0442 9.71 1.359 -0.0534 8.59 1.320 -0.0646 7.77 1.287 -0.0725 6.60 1.208 -0.0806 5.69 1.142 -0.0873 4.53 1.044 -0.0946 3.59 0.966 -0.1011 2.49 0.871 -0.1070 1.55 0.777 -0.1132 0.46 0.667 -0.1213 -0.60 0.555 -0.1278 -1.62 0.429 -0.1283 -2.74 0.336 -0.1313 -3.70 0.248 -0.1317 -4.78 0.131 -0.1295 -5.71 0.038 -0.1286 -6.97 -0.107 -0.1209 -7.79 -0.240 -0.0687 -8.60 -0.304 -0.0391 Tabulated from data in file cl02369.dat & reduced using program C06.01 Average Reynolds #: 299849 Number of angles of attack: 59 alpha / Cl / Cm -8.95 -0.326 -0.0310 -8.04 -0.265 -0.0677 -7.19 -0.140 -0.1145 -6.02 0.012 -0.1304 -5.07 0.111 -0.1306 -4.05 0.223 -0.1313 -3.04 0.335 -0.1330 -1.78 0.471 -0.1301 -0.97 0.553 -0.1263 0.11 0.656 -0.1199 1.20 0.770 -0.1145 2.24 0.865 -0.1088 3.49 0.979 -0.1022 4.75 1.086 -0.0948 5.48 1.153 -0.0902 6.25 1.215 -0.0852 7.40 1.297 -0.0767 8.35 1.345 -0.0679 9.29 1.383 -0.0585 10.27 1.416 -0.0501 11.34 1.443 -0.0424 12.32 1.453 -0.0390 13.33 1.435 -0.0451 14.28 1.421 -0.0559 14.99 1.167 -0.1648 16.04 1.097 -0.1714 17.06 1.102 -0.1764 18.00 1.100 -0.1838 19.00 1.132 -0.2001 20.08 1.203 -0.1926 19.56 1.156 -0.1944 18.65 1.129 -0.1914 17.64 1.100 -0.1825 16.53 1.051 -0.1740 15.68 1.043 -0.1742 14.70 1.088 -0.1658 13.71 1.165 -0.1598 12.87 1.436 -0.0398 11.86 1.443 -0.0408 10.63 1.423 -0.0486 9.81 1.397 -0.0534 8.68 1.357 -0.0625 7.77 1.308 -0.0706 6.64 1.237 -0.0793 5.65 1.159 -0.0858 4.58 1.070 -0.0929 2.88 0.922 -0.1030 2.31 0.872 -0.1063 1.30 0.776 -0.1124 0.48 0.693 -0.1168 -0.54 0.594 -0.1222 -1.64 0.483 -0.1284 -2.52 0.395 -0.1325 -3.53 0.281 -0.1317 -4.81 0.133 -0.1299 -5.61 0.052 -0.1294 -6.66 -0.058 -0.1291 -7.73 -0.224 -0.0861 -8.70 -0.320 -0.0398 Tabulated from data in file cl02371.dat & reduced using program C06.01 File 7037ef4.lft created using program C06.01 on Mon Feb 02 15:11:35 1998 :::::::::::::: A18T.LFT :::::::::::::: Airfoil: A18 Builder: R. Cooney Comment: Zigzag trip Type C (h = 0.023") @ 2% u.s. & 5% l.s. Number of Reynolds #'s: 3 Average Reynolds #: 99950 Number of angles of attack: 59 alpha / Cl / Cm -8.57 -0.526 0.0392 -7.80 -0.466 0.0372 -6.58 -0.426 0.0194 -5.60 -0.372 -0.0032 -4.81 -0.330 -0.0337 -3.78 -0.169 -0.0630 -2.64 -0.057 -0.0661 -1.49 0.051 -0.0688 -0.62 0.176 -0.0753 0.51 0.347 -0.0894 1.41 0.426 -0.0864 2.43 0.496 -0.0780 3.59 0.586 -0.0724 4.43 0.658 -0.0697 5.58 0.769 -0.0665 6.63 0.859 -0.0627 7.70 0.937 -0.0587 8.45 0.998 -0.0559 9.77 1.095 -0.0503 10.56 1.144 -0.0468 11.56 1.177 -0.0415 12.47 1.143 -0.0996 13.54 1.166 -0.1206 14.69 1.104 -0.1334 15.58 1.118 -0.1461 16.48 1.083 -0.1532 17.71 1.125 -0.1582 18.61 0.987 -0.1647 19.50 1.051 -0.1756 20.72 1.031 -0.1810 19.07 1.000 -0.1703 18.16 0.999 -0.1721 17.28 0.977 -0.1710 16.24 1.119 -0.1604 15.21 1.129 -0.1494 14.37 1.138 -0.1512 13.43 1.119 -0.1347 12.37 1.186 -0.1051 11.45 1.180 -0.0555 10.24 1.137 -0.0553 9.66 1.098 -0.0576 8.54 1.017 -0.0617 7.42 0.935 -0.0659 6.51 0.865 -0.0692 5.39 0.769 -0.0731 4.36 0.676 -0.0755 3.34 0.589 -0.0781 2.33 0.507 -0.0832 1.38 0.437 -0.0922 0.25 0.301 -0.0972 -0.96 0.123 -0.0822 -1.92 0.005 -0.0715 -2.77 -0.069 -0.0698 -3.78 -0.167 -0.0678 -4.86 -0.324 -0.0419 -5.80 -0.405 -0.0102 -6.93 -0.439 0.0088 -7.91 -0.482 0.0234 -8.66 -0.447 0.0325 Tabulated from data in file pg02558.dat & reduced using program C06.01 Average Reynolds #: 199932 Number of angles of attack: 59 alpha / Cl / Cm -9.05 -0.516 0.0494 -8.00 -0.509 0.0385 -7.03 -0.495 0.0262 -5.85 -0.443 0.0000 -4.79 -0.319 -0.0408 -3.60 -0.111 -0.0739 -2.76 0.004 -0.0823 -1.83 0.130 -0.0890 -0.64 0.238 -0.0845 0.76 0.361 -0.0807 1.30 0.413 -0.0793 2.48 0.525 -0.0773 3.35 0.609 -0.0749 4.64 0.728 -0.0721 5.43 0.798 -0.0699 6.38 0.884 -0.0672 7.47 0.975 -0.0637 8.45 1.050 -0.0598 9.45 1.127 -0.0567 10.50 1.187 -0.0513 11.71 1.241 -0.0454 12.48 1.249 -0.0426 13.45 1.254 -0.0627 14.67 1.163 -0.1007 15.26 1.242 -0.1529 16.37 1.187 -0.1577 17.33 1.169 -0.1681 18.24 1.137 -0.1718 19.22 0.996 -0.1710 20.18 1.001 -0.1695 19.36 0.993 -0.1729 18.55 0.981 -0.1761 17.58 1.130 -0.1794 16.40 1.135 -0.1650 15.44 1.177 -0.1648 14.34 1.211 -0.1326 13.74 1.246 -0.0628 12.70 1.244 -0.0443 11.78 1.232 -0.0456 10.60 1.188 -0.0504 9.62 1.124 -0.0540 8.47 1.046 -0.0579 7.62 0.983 -0.0609 6.50 0.885 -0.0640 5.37 0.802 -0.0690 4.23 0.718 -0.0741 3.46 0.622 -0.0749 2.37 0.520 -0.0772 1.00 0.388 -0.0806 0.21 0.316 -0.0822 -0.84 0.226 -0.0861 -2.01 0.112 -0.0902 -2.86 -0.018 -0.0804 -3.89 -0.143 -0.0718 -4.77 -0.310 -0.0471 -5.61 -0.426 -0.0052 -6.72 -0.489 0.0151 -7.60 -0.487 0.0318 -8.73 -0.499 0.0438 Tabulated from data in file pg02560.dat & reduced using program C06.01 Average Reynolds #: 299997 Number of angles of attack: 53 alpha / Cl / Cm -5.84 -0.435 -0.0138 -5.04 -0.292 -0.0586 -4.12 -0.132 -0.0841 -3.12 0.004 -0.0903 -2.05 0.097 -0.0871 -1.02 0.199 -0.0853 0.05 0.301 -0.0837 1.08 0.405 -0.0816 2.24 0.516 -0.0790 3.19 0.609 -0.0772 4.24 0.705 -0.0743 5.36 0.809 -0.0717 6.51 0.911 -0.0682 7.67 1.005 -0.0640 8.61 1.082 -0.0609 9.92 1.166 -0.0544 10.38 1.184 -0.0516 11.84 1.218 -0.0454 12.50 1.220 -0.0493 13.52 1.217 -0.0777 14.38 1.203 -0.1069 15.10 1.220 -0.1198 16.01 1.196 -0.1751 17.01 1.138 -0.1781 18.06 1.138 -0.1783 18.91 1.142 -0.1806 20.05 1.093 -0.1872 19.61 1.103 -0.1812 18.70 1.117 -0.1830 17.65 1.141 -0.1810 16.60 1.169 -0.1820 15.79 1.211 -0.1715 14.69 1.255 -0.1438 13.45 1.204 -0.0793 12.63 1.219 -0.0524 11.73 1.216 -0.0443 10.62 1.196 -0.0488 9.55 1.145 -0.0549 8.50 1.074 -0.0594 7.34 0.979 -0.0635 6.13 0.876 -0.0680 5.24 0.799 -0.0712 4.19 0.701 -0.0742 2.97 0.588 -0.0781 2.36 0.529 -0.0800 1.24 0.420 -0.0831 0.33 0.338 -0.0844 -0.82 0.219 -0.0872 -1.67 0.136 -0.0879 -2.67 0.040 -0.0905 -3.76 -0.082 -0.0886 -4.76 -0.218 -0.0804 -5.46 -0.379 -0.0332 Tabulated from data in file pg02562.dat & reduced using program C06.01 File a18t.lft created using program C06.01 on Mon Feb 02 15:11:35 1998 :::::::::::::: AVISTAR.LFT :::::::::::::: Airfoil: Avistar Builder: B. Champine Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 100900 Number of angles of attack: 49 alpha / Cl / Cm -6.37 -0.425 -0.0357 -5.04 -0.276 -0.0450 -4.04 -0.158 -0.0533 -3.04 -0.034 -0.0592 -2.04 0.067 -0.0545 -1.00 0.264 -0.0659 0.03 0.408 -0.0758 1.04 0.464 -0.0684 2.07 0.539 -0.0629 3.10 0.619 -0.0588 4.13 0.701 -0.0565 5.17 0.783 -0.0520 6.21 0.865 -0.0470 7.23 0.936 -0.0417 8.22 0.970 -0.0331 9.18 0.986 -0.0234 10.45 1.011 -0.0140 11.39 1.031 -0.0097 12.34 1.040 -0.0071 13.27 1.043 -0.0067 14.22 1.047 -0.0084 15.20 1.026 -0.0164 16.15 0.891 -0.0866 17.14 0.836 -0.0937 18.16 0.811 -0.0956 16.41 0.883 -0.0888 15.54 0.988 -0.0589 14.71 1.033 -0.0166 13.62 1.035 -0.0121 12.77 1.037 -0.0116 11.67 1.033 -0.0142 10.60 1.012 -0.0180 9.51 0.987 -0.0248 8.66 0.983 -0.0334 7.53 0.963 -0.0422 6.63 0.922 -0.0481 5.46 0.837 -0.0536 4.54 0.771 -0.0561 3.61 0.684 -0.0579 2.45 0.585 -0.0610 1.55 0.538 -0.0649 0.39 0.427 -0.0721 -0.47 0.370 -0.0760 -1.66 0.115 -0.0571 -2.52 0.022 -0.0617 -3.66 -0.101 -0.0618 -4.80 -0.248 -0.0525 -5.71 -0.349 -0.0434 -6.85 -0.462 -0.0350 Tabulated from data in file CL01117.DAT & reduced using program Q06.01L Average Reynolds #: 201600 Number of angles of attack: 53 alpha / Cl / Cm -6.36 -0.294 -0.0649 -4.90 -0.175 -0.0635 -4.14 -0.111 -0.0608 -3.07 -0.027 -0.0570 -1.97 0.068 -0.0513 -0.87 0.169 -0.0458 0.24 0.304 -0.0486 0.96 0.409 -0.0543 2.03 0.541 -0.0590 3.04 0.638 -0.0560 4.25 0.759 -0.0527 5.31 0.845 -0.0491 6.35 0.902 -0.0415 7.07 0.922 -0.0342 8.35 0.957 -0.0221 9.30 0.986 -0.0156 10.22 1.005 -0.0106 11.14 1.019 -0.0081 12.35 1.032 -0.0070 13.30 1.034 -0.0084 14.22 1.033 -0.0124 15.14 1.033 -0.0202 16.17 0.863 -0.0951 17.18 0.825 -0.1004 18.26 0.838 -0.1063 19.36 0.851 -0.1095 20.40 0.869 -0.1118 18.41 0.836 -0.1087 17.38 0.827 -0.1052 16.39 0.843 -0.0988 15.77 0.895 -0.0907 14.65 1.038 -0.0179 13.53 1.031 -0.0120 12.77 1.030 -0.0101 11.69 1.028 -0.0093 10.63 1.011 -0.0108 9.60 0.990 -0.0153 8.55 0.962 -0.0221 7.45 0.928 -0.0309 6.62 0.913 -0.0408 5.40 0.861 -0.0505 4.49 0.793 -0.0538 3.59 0.723 -0.0558 2.47 0.595 -0.0594 1.59 0.509 -0.0611 0.31 0.321 -0.0498 -0.65 0.196 -0.0454 -1.61 0.111 -0.0486 -2.84 0.010 -0.0554 -3.82 -0.076 -0.0591 -4.82 -0.150 -0.0624 -5.85 -0.240 -0.0656 -6.90 -0.351 -0.0649 Tabulated from data in file CL01119.DAT & reduced using program Q06.01L Average Reynolds #: 302500 Number of angles of attack: 53 alpha / Cl / Cm -6.29 -0.293 -0.0605 -5.13 -0.215 -0.0584 -3.90 -0.106 -0.0554 -2.93 -0.019 -0.0539 -1.89 0.078 -0.0508 -0.77 0.178 -0.0463 0.03 0.269 -0.0444 1.19 0.469 -0.0529 2.27 0.607 -0.0581 3.40 0.711 -0.0558 4.15 0.783 -0.0538 5.30 0.863 -0.0472 6.39 0.904 -0.0374 7.11 0.931 -0.0307 8.35 0.977 -0.0205 9.24 1.003 -0.0149 10.13 1.023 -0.0105 11.23 1.039 -0.0075 12.07 1.046 -0.0076 13.15 1.057 -0.0093 14.34 1.097 -0.0146 15.18 1.104 -0.0484 16.18 0.966 -0.0917 17.22 0.892 -0.1030 18.17 0.892 -0.1075 19.09 0.903 -0.1134 20.17 0.916 -0.1263 18.22 0.910 -0.1091 17.54 0.890 -0.1046 16.50 0.921 -0.0960 15.62 1.084 -0.0750 14.75 1.118 -0.0187 13.72 1.093 -0.0129 12.64 1.070 -0.0092 11.75 1.063 -0.0079 10.60 1.048 -0.0098 9.70 1.029 -0.0131 8.74 1.003 -0.0186 7.45 0.956 -0.0280 6.64 0.926 -0.0356 5.44 0.880 -0.0462 4.51 0.822 -0.0527 3.53 0.740 -0.0552 2.48 0.635 -0.0579 1.42 0.512 -0.0557 0.42 0.360 -0.0474 -0.78 0.208 -0.0463 -1.86 0.106 -0.0505 -2.64 0.042 -0.0526 -3.74 -0.061 -0.0546 -4.82 -0.165 -0.0574 -5.86 -0.257 -0.0601 -6.88 -0.336 -0.0635 Tabulated from data in file CL01121.DAT & reduced using program Q06.01L Average Reynolds #: 403100 Number of angles of attack: 53 alpha / Cl / Cm -6.56 -0.333 -0.0596 -4.94 -0.198 -0.0559 -4.00 -0.110 -0.0541 -3.03 -0.015 -0.0526 -1.97 0.079 -0.0508 -1.01 0.184 -0.0474 0.07 0.320 -0.0451 1.25 0.466 -0.0480 2.05 0.577 -0.0521 3.26 0.723 -0.0567 4.13 0.796 -0.0536 5.59 0.870 -0.0421 6.15 0.894 -0.0371 7.55 0.950 -0.0256 8.40 0.975 -0.0192 9.19 0.998 -0.0147 10.33 1.022 -0.0105 11.41 1.040 -0.0098 12.47 1.062 -0.0122 13.18 1.102 -0.0126 14.44 1.149 -0.0171 15.36 1.102 -0.0599 16.19 1.031 -0.0843 17.08 0.928 -0.0997 18.17 0.958 -0.1094 19.00 0.967 -0.1219 20.01 0.955 -0.1341 18.46 0.962 -0.1168 17.42 0.954 -0.1023 16.33 0.965 -0.0926 15.34 1.061 -0.0645 14.81 1.208 -0.0280 13.56 1.157 -0.0155 12.70 1.106 -0.0133 11.58 1.072 -0.0091 10.76 1.056 -0.0090 9.65 1.026 -0.0113 8.48 0.990 -0.0167 7.53 0.964 -0.0240 6.46 0.929 -0.0325 5.27 0.874 -0.0431 4.38 0.827 -0.0501 3.42 0.752 -0.0544 2.42 0.630 -0.0534 1.49 0.504 -0.0489 0.13 0.325 -0.0453 -0.77 0.224 -0.0466 -1.89 0.094 -0.0507 -2.78 0.017 -0.0524 -3.92 -0.099 -0.0541 -4.72 -0.174 -0.0551 -5.88 -0.282 -0.0578 -7.01 -0.372 -0.0607 Tabulated from data in file CL01123.DAT & reduced using program Q06.01L Average Reynolds #: 504100 Number of angles of attack: 51 alpha / Cl / Cm -7.28 -0.394 -0.0618 -5.14 -0.229 -0.0594 -3.87 -0.113 -0.0581 -2.95 -0.025 -0.0569 -1.99 0.064 -0.0568 -0.95 0.167 -0.0543 0.16 0.282 -0.0522 1.33 0.410 -0.0516 2.50 0.560 -0.0550 3.16 0.645 -0.0588 4.39 0.764 -0.0593 5.67 0.831 -0.0509 6.59 0.870 -0.0433 7.57 0.913 -0.0354 8.45 0.947 -0.0289 9.29 0.974 -0.0238 10.63 1.007 -0.0194 11.34 1.025 -0.0183 12.57 1.063 -0.0200 13.81 1.138 -0.0206 14.54 1.185 -0.0204 15.61 1.169 -0.0449 16.27 1.031 -0.0756 17.41 0.963 -0.1004 18.06 0.934 -0.1041 19.12 0.995 -0.1191 17.60 0.967 -0.1015 16.59 0.988 -0.0901 15.62 1.171 -0.0463 14.33 1.199 -0.0173 13.44 1.147 -0.0159 12.55 1.117 -0.0119 11.68 1.095 -0.0087 10.23 1.064 -0.0096 9.67 1.044 -0.0118 8.08 0.983 -0.0215 7.38 0.955 -0.0263 6.01 0.892 -0.0374 5.17 0.852 -0.0452 4.10 0.776 -0.0528 3.18 0.674 -0.0524 2.37 0.568 -0.0487 0.83 0.386 -0.0462 -0.01 0.302 -0.0474 -0.80 0.219 -0.0485 -1.61 0.139 -0.0509 -2.91 0.013 -0.0526 -4.12 -0.108 -0.0541 -4.84 -0.177 -0.0551 -6.15 -0.291 -0.0574 -6.87 -0.350 -0.0596 Tabulated from data in file CL01766.DAT & reduced using program Q06.01L File AVISTAR.LFT created on 10-24-1997 at 19:34:41 using program FORMAT :::::::::::::: BW3.LFT :::::::::::::: Airfoil: BW-3 Builder: M. Allen Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 60000 Number of angles of attack: 49 alpha / Cl / Cm -4.77 -0.259 -0.0074 -3.75 -0.193 -0.0220 -2.71 -0.110 -0.0406 -1.66 -0.020 -0.0605 -0.60 0.116 -0.0746 0.47 0.276 -0.0925 1.50 0.414 -0.1079 2.59 0.586 -0.1155 3.64 0.738 -0.1272 4.67 0.890 -0.1264 5.70 0.985 -0.1248 6.85 1.064 -0.1063 7.41 1.092 -0.0982 8.89 1.179 -0.0918 9.87 1.236 -0.0809 10.84 1.268 -0.0733 11.49 1.298 -0.0653 12.89 1.317 -0.0766 13.84 1.261 -0.1365 14.85 1.207 -0.1679 15.87 1.189 -0.1743 16.87 1.211 -0.1825 17.87 1.196 -0.1852 18.53 1.239 -0.1869 19.51 1.241 -0.1926 17.62 1.225 -0.1880 16.68 1.166 -0.1826 15.67 1.158 -0.1733 14.80 1.221 -0.1666 13.90 1.299 -0.1398 13.00 1.327 -0.0898 11.64 1.318 -0.0766 10.77 1.294 -0.0850 9.91 1.253 -0.0864 8.93 1.204 -0.0953 7.92 1.150 -0.0994 6.53 1.071 -0.1159 5.99 1.040 -0.1244 4.52 0.928 -0.1371 3.54 0.775 -0.1412 2.61 0.616 -0.1302 1.71 0.486 -0.1193 0.37 0.303 -0.1058 -0.51 0.173 -0.0905 -1.50 0.024 -0.0743 -2.43 -0.091 -0.0544 -3.35 -0.178 -0.0339 -4.72 -0.256 -0.0068 -5.64 -0.295 0.0060 Tabulated from data in file PG01722.DAT & reduced using program Q06.01L Average Reynolds #: 100000 Number of angles of attack: 49 alpha / Cl / Cm -5.14 -0.351 0.0208 -3.60 -0.286 -0.0044 -2.49 -0.198 -0.0267 -1.47 -0.036 -0.0563 -0.40 0.151 -0.0876 0.73 0.372 -0.1128 1.86 0.565 -0.1294 2.44 0.651 -0.1353 3.56 0.794 -0.1360 4.68 0.893 -0.1276 5.82 0.987 -0.1176 6.46 1.036 -0.1125 7.54 1.102 -0.1036 8.61 1.166 -0.0964 9.67 1.233 -0.0904 10.72 1.291 -0.0836 11.75 1.327 -0.0775 12.80 1.350 -0.0803 13.80 1.343 -0.1492 14.79 1.178 -0.1793 15.38 1.174 -0.1859 17.06 1.149 -0.1903 17.66 1.156 -0.1924 18.82 1.165 -0.1946 19.96 1.193 -0.1980 17.83 1.172 -0.1976 16.74 1.144 -0.1920 15.71 1.140 -0.1859 14.71 1.216 -0.1848 13.83 1.333 -0.1495 12.87 1.355 -0.0922 11.94 1.335 -0.0843 10.97 1.303 -0.0882 9.56 1.229 -0.0966 9.00 1.193 -0.1005 7.53 1.104 -0.1099 6.94 1.074 -0.1161 5.91 0.998 -0.1259 4.87 0.916 -0.1349 3.83 0.831 -0.1440 2.80 0.711 -0.1468 1.79 0.558 -0.1382 0.29 0.288 -0.1108 -0.25 0.181 -0.0985 -1.79 -0.098 -0.0547 -2.74 -0.215 -0.0301 -3.68 -0.279 -0.0093 -4.61 -0.330 0.0083 -5.55 -0.358 0.0193 Tabulated from data in file PG01514.DAT & reduced using program Q06.01L Average Reynolds #: 200100 Number of angles of attack: 49 alpha / Cl / Cm -4.77 -0.335 0.0109 -3.70 -0.277 -0.0082 -2.73 -0.116 -0.0491 -1.56 0.126 -0.0947 -0.48 0.368 -0.1265 0.45 0.529 -0.1375 1.55 0.656 -0.1352 2.67 0.769 -0.1317 3.84 0.885 -0.1269 4.59 0.959 -0.1246 5.88 1.065 -0.1172 6.56 1.107 -0.1126 7.82 1.193 -0.1046 8.53 1.241 -0.1012 9.72 1.310 -0.0932 10.79 1.361 -0.0860 11.84 1.413 -0.0882 12.73 1.389 -0.1314 13.67 1.333 -0.1759 14.59 1.240 -0.1950 15.59 1.206 -0.1991 16.63 1.191 -0.2008 17.63 1.182 -0.2011 18.64 1.207 -0.2036 19.69 1.201 -0.2039 17.54 1.182 -0.2013 16.85 1.178 -0.2008 15.79 1.174 -0.1969 14.70 1.234 -0.1967 13.67 1.321 -0.1783 13.16 1.363 -0.1609 11.86 1.413 -0.0921 10.83 1.363 -0.0893 9.78 1.313 -0.0959 8.71 1.250 -0.1025 7.60 1.175 -0.1087 6.45 1.099 -0.1155 5.71 1.058 -0.1211 4.47 0.949 -0.1269 3.72 0.877 -0.1303 2.45 0.753 -0.1349 1.75 0.682 -0.1375 0.62 0.561 -0.1411 -0.31 0.401 -0.1335 -1.38 0.182 -0.1052 -2.51 -0.055 -0.0638 -3.51 -0.246 -0.0198 -4.53 -0.322 0.0029 -5.53 -0.373 0.0190 Tabulated from data in file PG01516.DAT & reduced using program Q06.01L Average Reynolds #: 299500 Number of angles of attack: 37 alpha / Cl / Cm -2.99 -0.075 -0.0614 -1.78 0.169 -0.1043 -0.50 0.417 -0.1286 0.30 0.521 -0.1303 1.60 0.670 -0.1288 2.45 0.763 -0.1273 3.78 0.903 -0.1254 4.65 0.988 -0.1224 5.62 1.059 -0.1175 6.67 1.135 -0.1120 7.63 1.207 -0.1074 8.66 1.279 -0.1017 9.78 1.342 -0.0940 10.90 1.407 -0.0873 12.01 1.440 -0.0917 12.70 1.418 -0.1227 13.31 1.380 -0.1560 14.42 1.313 -0.1889 15.49 1.242 -0.1991 14.07 1.326 -0.1809 13.11 1.393 -0.1486 11.72 1.443 -0.0903 10.68 1.390 -0.0901 10.06 1.355 -0.0927 8.82 1.288 -0.1015 7.61 1.204 -0.1076 6.94 1.154 -0.1111 5.81 1.071 -0.1170 4.70 0.990 -0.1232 3.67 0.890 -0.1268 2.66 0.783 -0.1294 1.68 0.676 -0.1316 0.78 0.574 -0.1325 -0.21 0.457 -0.1316 -1.47 0.252 -0.1168 -2.18 0.086 -0.0931 -3.45 -0.166 -0.0417 Tabulated from data in file PG01518.DAT & reduced using program Q06.01L Average Reynolds #: 399300 Number of angles of attack: 33 alpha / Cl / Cm -3.07 -0.038 -0.0707 -1.95 0.217 -0.1131 -0.76 0.405 -0.1263 0.39 0.554 -0.1293 1.44 0.677 -0.1286 2.51 0.796 -0.1274 3.39 0.889 -0.1260 4.39 0.984 -0.1228 5.53 1.069 -0.1169 6.68 1.160 -0.1125 7.54 1.224 -0.1077 8.86 1.312 -0.1001 9.80 1.365 -0.0937 10.75 1.431 -0.0890 11.66 1.441 -0.0924 12.33 1.421 -0.1238 13.31 1.401 -0.1636 12.19 1.430 -0.1159 10.67 1.420 -0.0889 9.49 1.344 -0.0924 8.84 1.308 -0.0966 7.70 1.230 -0.1040 6.64 1.150 -0.1096 5.55 1.064 -0.1143 4.52 0.989 -0.1200 3.60 0.904 -0.1235 2.70 0.810 -0.1259 1.88 0.720 -0.1275 0.68 0.582 -0.1289 -0.41 0.445 -0.1278 -1.42 0.309 -0.1221 -2.27 0.143 -0.1034 -3.32 -0.099 -0.0574 Tabulated from data in file PG01520.DAT & reduced using program Q06.01L File BW3.LFT created on 10-24-1997 at 19:34:41 using program FORMAT :::::::::::::: BW3T.LFT :::::::::::::: Airfoil: BW-3 Builder: M. Allen Comment: Zig-Zag trip type "C" @ u.s. x/c = 2% & l.s. x/c = 5% Number of Reynolds #'s: 4 Average Reynolds #: 100000 Number of angles of attack: 49 alpha / Cl / Cm -5.04 -0.342 0.0178 -3.64 -0.284 -0.0047 -2.20 -0.159 -0.0366 -1.89 -0.109 -0.0468 -0.36 0.218 -0.0950 0.51 0.439 -0.1182 2.03 0.582 -0.1151 2.48 0.628 -0.1144 4.13 0.785 -0.1108 3.73 0.748 -0.1096 6.12 0.955 -0.1043 6.44 0.980 -0.1006 7.98 1.089 -0.0971 8.84 1.149 -0.0925 9.69 1.208 -0.0883 10.72 1.276 -0.0826 11.74 1.322 -0.0803 12.71 1.295 -0.1222 13.60 1.218 -0.1673 14.59 1.155 -0.1751 15.62 1.160 -0.1858 16.66 1.158 -0.1938 17.66 1.127 -0.1918 18.75 1.150 -0.1953 19.82 1.184 -0.2034 17.38 1.135 -0.1935 16.82 1.138 -0.1943 15.81 1.154 -0.1892 14.83 1.149 -0.1805 13.87 1.213 -0.1633 13.00 1.267 -0.1476 11.70 1.327 -0.0832 10.79 1.286 -0.0844 9.83 1.222 -0.0905 8.92 1.160 -0.0950 7.56 1.063 -0.1025 6.54 0.991 -0.1054 5.93 0.943 -0.1082 4.48 0.820 -0.1122 3.89 0.769 -0.1151 2.45 0.626 -0.1178 1.48 0.528 -0.1210 0.54 0.434 -0.1244 -0.53 0.162 -0.0942 -1.50 -0.046 -0.0650 -2.44 -0.189 -0.0361 -3.74 -0.280 -0.0109 -4.69 -0.335 0.0090 -5.63 -0.342 0.0178 Tabulated from data in file PG01772.DAT & reduced using program Q06.01L Average Reynolds #: 200000 Number of angles of attack: 49 alpha / Cl / Cm -4.92 -0.362 0.0165 -3.55 -0.287 -0.0067 -2.59 -0.091 -0.0518 -1.56 0.100 -0.0841 -0.49 0.263 -0.1029 0.58 0.404 -0.1101 1.35 0.564 -0.1155 2.49 0.694 -0.1146 3.65 0.807 -0.1124 4.80 0.912 -0.1093 5.47 0.969 -0.1070 6.62 1.067 -0.1026 7.77 1.151 -0.0971 8.84 1.222 -0.0917 9.89 1.297 -0.0874 10.93 1.369 -0.0847 11.51 1.390 -0.0909 12.76 1.358 -0.1392 13.62 1.344 -0.1605 14.93 1.237 -0.1809 15.85 1.215 -0.1925 16.79 1.176 -0.1938 17.76 1.165 -0.1982 18.70 1.176 -0.1988 19.65 1.203 -0.2036 17.68 1.172 -0.1987 16.70 1.156 -0.1954 15.75 1.260 -0.1948 14.78 1.258 -0.1848 13.79 1.312 -0.1763 12.95 1.378 -0.1447 12.06 1.350 -0.1145 10.76 1.358 -0.0861 9.80 1.294 -0.0896 8.77 1.223 -0.0947 7.69 1.147 -0.1000 6.62 1.066 -0.1042 5.95 1.011 -0.1067 4.83 0.915 -0.1108 3.72 0.811 -0.1136 2.63 0.708 -0.1158 1.44 0.583 -0.1171 0.56 0.423 -0.1127 -0.53 0.283 -0.1060 -1.51 0.132 -0.0904 -2.54 -0.052 -0.0608 -3.43 -0.256 -0.0170 -4.78 -0.350 0.0108 -5.65 -0.379 0.0229 Tabulated from data in file PG01774.DAT & reduced using program Q06.01L Average Reynolds #: 300200 Number of angles of attack: 41 alpha / Cl / Cm -5.07 -0.380 0.0172 -3.91 -0.226 -0.0259 -2.71 -0.046 -0.0644 -1.81 0.099 -0.0891 -0.93 0.289 -0.1092 0.65 0.530 -0.1202 1.52 0.625 -0.1193 2.43 0.720 -0.1182 3.79 0.855 -0.1154 4.38 0.910 -0.1136 5.82 1.034 -0.1092 6.88 1.118 -0.1050 7.49 1.163 -0.1018 9.00 1.265 -0.0937 9.64 1.302 -0.0899 10.77 1.385 -0.0851 11.73 1.413 -0.0997 12.47 1.403 -0.1231 13.64 1.361 -0.1672 14.55 1.302 -0.1838 15.53 1.317 -0.1959 13.68 1.374 -0.1628 12.98 1.404 -0.1393 11.80 1.423 -0.1025 10.97 1.397 -0.0864 9.44 1.291 -0.0925 8.75 1.248 -0.0965 7.57 1.168 -0.1030 6.96 1.122 -0.1056 5.80 1.031 -0.1106 4.68 0.934 -0.1151 3.64 0.837 -0.1173 2.64 0.738 -0.1198 1.60 0.632 -0.1214 0.61 0.526 -0.1223 -0.33 0.384 -0.1167 -1.16 0.253 -0.1080 -2.58 -0.014 -0.0721 -3.41 -0.152 -0.0438 -4.51 -0.318 -0.0012 -5.34 -0.422 0.0257 Tabulated from data in file PG01776.DAT & reduced using program Q06.01L Average Reynolds #: 400600 Number of angles of attack: 37 alpha / Cl / Cm -4.90 -0.325 0.0037 -3.86 -0.224 -0.0248 -3.01 -0.075 -0.0613 -1.93 0.170 -0.1019 -0.65 0.377 -0.1170 0.33 0.522 -0.1223 1.47 0.645 -0.1212 2.38 0.740 -0.1196 3.66 0.867 -0.1173 4.38 0.934 -0.1149 5.52 1.034 -0.1111 6.73 1.131 -0.1066 7.61 1.196 -0.1025 8.56 1.260 -0.0976 9.94 1.340 -0.0896 10.96 1.400 -0.0848 11.76 1.421 -0.0989 12.40 1.428 -0.1219 13.39 1.393 -0.1550 11.85 1.426 -0.1014 10.66 1.377 -0.0823 9.52 1.314 -0.0877 8.86 1.276 -0.0927 7.75 1.203 -0.0977 6.68 1.125 -0.1035 5.66 1.042 -0.1073 4.64 0.957 -0.1121 3.70 0.869 -0.1152 2.80 0.780 -0.1178 1.49 0.645 -0.1196 0.64 0.555 -0.1214 -0.54 0.399 -0.1201 -1.25 0.288 -0.1131 -2.20 0.080 -0.0899 -3.35 -0.141 -0.0461 -4.61 -0.306 -0.0046 -5.34 -0.359 0.0130 Tabulated from data in file PG01778.DAT & reduced using program Q06.01L File BW3T.LFT created on 10-24-1997 at 19:34:41 using program FORMAT :::::::::::::: CLARKYB.LFT :::::::::::::: Airfoil: Clark-Y (B) Builder: J. Robertson Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 60900 Number of angles of attack: 49 alpha / Cl / Cm -6.02 -0.415 -0.0336 -4.47 -0.324 -0.0455 -3.89 -0.282 -0.0469 -2.35 -0.138 -0.0508 -1.78 -0.073 -0.0522 -0.73 0.026 -0.0521 0.31 0.125 -0.0543 1.38 0.258 -0.0652 2.42 0.352 -0.0704 3.48 0.498 -0.0776 4.54 0.632 -0.0801 5.57 0.708 -0.0769 6.62 0.804 -0.0734 7.67 0.901 -0.0685 8.67 0.984 -0.0626 9.68 1.061 -0.0555 10.67 1.126 -0.0511 11.65 1.182 -0.0442 12.62 1.210 -0.0395 13.61 1.236 -0.0322 14.59 1.250 -0.0321 15.54 0.897 -0.1102 16.61 0.853 -0.1178 17.65 0.934 -0.1294 18.81 0.939 -0.1340 16.92 0.877 -0.1240 15.84 0.842 -0.1155 14.90 0.821 -0.1066 13.95 0.794 -0.0980 12.49 0.745 -0.0912 12.00 0.753 -0.0908 10.60 0.781 -0.0860 9.76 1.071 -0.0639 8.86 1.015 -0.0627 7.94 0.950 -0.0667 6.52 0.828 -0.0747 5.56 0.734 -0.0773 4.62 0.654 -0.0808 3.67 0.549 -0.0824 2.70 0.417 -0.0789 1.75 0.323 -0.0735 0.80 0.204 -0.0661 -0.60 0.063 -0.0577 -1.51 -0.028 -0.0543 -2.47 -0.133 -0.0507 -3.38 -0.216 -0.0467 -4.34 -0.302 -0.0439 -5.82 -0.400 -0.0359 -6.33 -0.422 -0.0299 Tabulated from data in file PG01708.DAT & reduced using program Q06.01L Average Reynolds #: 100700 Number of angles of attack: 49 alpha / Cl / Cm -6.04 -0.445 -0.0241 -4.39 -0.296 -0.0483 -3.72 -0.210 -0.0531 -2.56 -0.080 -0.0610 -1.37 0.065 -0.0704 -0.30 0.179 -0.0740 0.28 0.263 -0.0799 1.37 0.385 -0.0822 2.50 0.513 -0.0814 3.63 0.627 -0.0773 4.77 0.741 -0.0720 5.89 0.849 -0.0673 6.49 0.905 -0.0649 7.58 0.994 -0.0599 8.65 1.076 -0.0559 9.71 1.153 -0.0524 10.78 1.230 -0.0487 11.85 1.265 -0.0393 12.91 1.280 -0.0303 13.97 1.299 -0.0253 14.54 1.301 -0.0230 15.64 1.282 -0.0225 16.65 0.902 -0.1192 17.86 0.939 -0.1275 18.48 0.950 -0.1283 16.42 0.912 -0.1244 15.80 0.913 -0.1199 14.79 0.957 -0.1138 13.87 1.301 -0.0305 12.88 1.284 -0.0339 11.92 1.270 -0.0416 10.96 1.251 -0.0508 9.99 1.183 -0.0547 9.02 1.114 -0.0584 7.54 1.003 -0.0643 7.00 0.962 -0.0665 5.47 0.828 -0.0729 4.91 0.774 -0.0754 3.86 0.668 -0.0800 2.83 0.565 -0.0850 1.80 0.451 -0.0877 0.78 0.334 -0.0862 -0.22 0.204 -0.0796 -1.24 0.083 -0.0740 -2.75 -0.091 -0.0620 -3.27 -0.145 -0.0600 -4.37 -0.281 -0.0505 -5.35 -0.387 -0.0418 -6.47 -0.460 -0.0148 Tabulated from data in file PG01711.DAT & reduced using program Q06.01L Average Reynolds #: 201100 Number of angles of attack: 49 alpha / Cl / Cm -6.05 -0.339 -0.0620 -4.22 -0.109 -0.0832 -3.48 -0.015 -0.0881 -2.27 0.105 -0.0881 -1.62 0.168 -0.0865 -0.31 0.296 -0.0819 0.31 0.369 -0.0830 1.49 0.501 -0.0841 2.69 0.614 -0.0808 3.89 0.725 -0.0774 4.52 0.785 -0.0755 5.82 0.900 -0.0714 7.00 0.999 -0.0677 7.66 1.054 -0.0654 8.79 1.146 -0.0619 9.85 1.232 -0.0590 11.00 1.288 -0.0496 11.63 1.298 -0.0432 12.73 1.312 -0.0338 13.78 1.321 -0.0278 14.82 1.322 -0.0261 15.96 1.325 -0.0286 16.58 1.319 -0.0321 17.19 0.937 -0.1341 18.99 0.975 -0.1395 16.70 0.919 -0.1285 15.44 0.939 -0.1239 14.79 1.052 -0.1198 13.93 1.321 -0.0278 12.92 1.314 -0.0328 11.96 1.301 -0.0404 10.98 1.291 -0.0507 9.97 1.243 -0.0590 8.87 1.158 -0.0631 7.75 1.067 -0.0668 6.65 0.977 -0.0708 5.56 0.882 -0.0745 4.95 0.828 -0.0767 3.81 0.726 -0.0806 2.57 0.609 -0.0833 1.86 0.543 -0.0852 0.73 0.437 -0.0881 -0.41 0.287 -0.0835 -1.54 0.181 -0.0875 -2.25 0.114 -0.0883 -3.49 -0.009 -0.0889 -4.67 -0.165 -0.0772 -5.39 -0.255 -0.0708 -6.52 -0.408 -0.0289 Tabulated from data in file PG01714.DAT & reduced using program Q06.01L Average Reynolds #: 301500 Number of angles of attack: 49 alpha / Cl / Cm -5.93 -0.241 -0.0841 -4.42 -0.096 -0.0857 -3.43 -0.009 -0.0833 -2.37 0.088 -0.0819 -1.35 0.186 -0.0797 -0.29 0.287 -0.0772 0.34 0.382 -0.0821 1.41 0.507 -0.0839 2.54 0.618 -0.0814 3.72 0.731 -0.0786 4.39 0.790 -0.0771 5.73 0.905 -0.0723 7.00 1.015 -0.0692 7.68 1.074 -0.0674 8.86 1.177 -0.0633 10.05 1.260 -0.0571 10.63 1.286 -0.0521 11.66 1.309 -0.0422 12.71 1.331 -0.0344 13.72 1.348 -0.0296 14.72 1.354 -0.0283 15.76 1.349 -0.0318 16.78 1.340 -0.0374 17.84 1.311 -0.0458 18.89 1.291 -0.0542 16.96 1.333 -0.0385 15.95 1.349 -0.0337 15.05 1.353 -0.0289 14.07 1.349 -0.0280 12.68 1.330 -0.0335 12.12 1.317 -0.0374 10.67 1.286 -0.0505 9.66 1.232 -0.0581 8.61 1.151 -0.0634 7.96 1.095 -0.0653 6.83 0.997 -0.0688 5.61 0.893 -0.0720 4.84 0.827 -0.0746 3.47 0.703 -0.0789 2.80 0.641 -0.0809 1.58 0.521 -0.0838 0.37 0.388 -0.0825 -0.23 0.295 -0.0773 -1.37 0.185 -0.0800 -2.52 0.078 -0.0827 -3.73 -0.034 -0.0842 -4.32 -0.087 -0.0857 -5.40 -0.186 -0.0862 -6.47 -0.292 -0.0799 Tabulated from data in file PG01716.DAT & reduced using program Q06.01L Average Reynolds #: 401900 Number of angles of attack: 49 alpha / Cl / Cm -6.01 -0.237 -0.0857 -4.42 -0.105 -0.0815 -3.77 -0.043 -0.0809 -2.53 0.074 -0.0791 -1.36 0.191 -0.0783 -0.64 0.262 -0.0773 0.63 0.406 -0.0771 1.87 0.560 -0.0815 2.71 0.640 -0.0793 3.59 0.722 -0.0772 5.01 0.848 -0.0726 5.89 0.924 -0.0702 6.76 1.001 -0.0677 7.63 1.077 -0.0655 9.37 1.217 -0.0587 9.04 1.191 -0.0582 11.48 1.304 -0.0428 10.80 1.286 -0.0454 12.93 1.335 -0.0329 13.69 1.344 -0.0303 15.02 1.350 -0.0330 15.84 1.349 -0.0365 17.28 1.329 -0.0470 17.85 1.306 -0.0504 18.69 1.299 -0.0564 16.69 1.337 -0.0423 15.93 1.349 -0.0368 14.68 1.351 -0.0306 13.95 1.346 -0.0282 12.61 1.327 -0.0312 11.91 1.313 -0.0354 10.56 1.277 -0.0467 9.70 1.234 -0.0526 8.86 1.176 -0.0571 7.24 1.036 -0.0633 7.62 1.074 -0.0643 5.00 0.842 -0.0707 5.80 0.915 -0.0695 3.22 0.685 -0.0772 2.84 0.650 -0.0785 1.31 0.502 -0.0828 0.53 0.387 -0.0761 -0.27 0.295 -0.0764 -1.71 0.154 -0.0789 -2.54 0.071 -0.0795 -3.31 -0.004 -0.0806 -4.65 -0.127 -0.0823 -5.50 -0.198 -0.0847 -6.71 -0.304 -0.0729 Tabulated from data in file PG01718.DAT & reduced using program Q06.01L File CLARKYB.LFT created on 10-24-1997 at 19:34:41 using program FORMAT :::::::::::::: CLARKYBT.LFT :::::::::::::: Airfoil: Clark-Y (B) Builder: J. Robertson Comment: Zig-Zag trip type "C" @ u.s. x/c = 2% & l.s. x/c = 5% (h = 0.023") Number of Reynolds #'s: 4 Average Reynolds #: 100600 Number of angles of attack: 49 alpha / Cl / Cm -5.76 -0.391 -0.0379 -4.56 -0.278 -0.0511 -3.38 -0.152 -0.0598 -2.73 -0.086 -0.0624 -1.53 0.057 -0.0711 -0.34 0.227 -0.0772 0.84 0.389 -0.0837 1.55 0.503 -0.0833 2.77 0.603 -0.0738 3.44 0.651 -0.0679 4.72 0.726 -0.0591 5.96 0.803 -0.0519 6.63 0.852 -0.0496 7.87 0.936 -0.0441 8.52 0.982 -0.0413 9.74 1.050 -0.0354 10.93 1.098 -0.0299 11.50 1.123 -0.0286 12.61 1.130 -0.0273 13.75 1.145 -0.0296 14.93 1.159 -0.0328 15.56 1.175 -0.0355 16.69 0.918 -0.1270 17.89 0.962 -0.1334 18.54 0.967 -0.1357 16.29 0.937 -0.1369 15.71 0.931 -0.1098 14.67 1.165 -0.0376 13.67 1.150 -0.0329 12.63 1.134 -0.0320 12.06 1.129 -0.0318 11.02 1.107 -0.0334 9.50 1.042 -0.0389 8.94 1.015 -0.0423 7.88 0.949 -0.0471 6.80 0.875 -0.0515 5.71 0.799 -0.0580 4.62 0.731 -0.0641 3.99 0.696 -0.0688 2.89 0.623 -0.0767 1.81 0.541 -0.0851 0.73 0.391 -0.0890 -0.36 0.243 -0.0826 -1.40 0.096 -0.0776 -2.44 -0.036 -0.0689 -3.48 -0.145 -0.0622 -4.57 -0.257 -0.0534 -5.68 -0.371 -0.0395 -6.77 -0.412 -0.0093 Tabulated from data in file PG01751.DAT & reduced using program Q06.01L Average Reynolds #: 201400 Number of angles of attack: 49 alpha / Cl / Cm -5.91 -0.334 -0.0648 -4.64 -0.180 -0.0759 -3.37 -0.009 -0.0860 -2.67 0.068 -0.0864 -1.35 0.186 -0.0805 -0.64 0.251 -0.0771 0.63 0.366 -0.0717 1.89 0.469 -0.0660 2.60 0.524 -0.0632 3.89 0.627 -0.0593 4.56 0.681 -0.0571 5.85 0.781 -0.0527 6.50 0.828 -0.0499 7.72 0.912 -0.0444 8.89 0.983 -0.0390 9.52 1.014 -0.0358 10.68 1.054 -0.0313 11.86 1.079 -0.0301 12.99 1.098 -0.0354 13.60 1.096 -0.0392 14.79 1.104 -0.0513 15.94 1.111 -0.0585 16.54 1.124 -0.0610 17.53 0.931 -0.1310 18.68 0.932 -0.1335 16.50 1.137 -0.0899 15.95 1.138 -0.0691 14.85 1.110 -0.0521 13.81 1.097 -0.0413 12.78 1.097 -0.0337 11.74 1.081 -0.0324 10.71 1.054 -0.0335 9.67 1.015 -0.0375 8.60 0.959 -0.0412 8.01 0.924 -0.0436 6.90 0.850 -0.0485 5.80 0.777 -0.0533 4.64 0.692 -0.0572 3.45 0.598 -0.0612 2.82 0.549 -0.0634 1.68 0.459 -0.0686 0.49 0.353 -0.0730 -0.16 0.300 -0.0767 -1.36 0.190 -0.0814 -2.60 0.077 -0.0873 -3.33 0.002 -0.0869 -4.60 -0.159 -0.0784 -5.86 -0.321 -0.0653 -6.50 -0.417 -0.0331 Tabulated from data in file PG01754.DAT & reduced using program Q06.01L Average Reynolds #: 301800 Number of angles of attack: 49 alpha / Cl / Cm -5.84 -0.243 -0.0841 -4.79 -0.131 -0.0863 -3.73 -0.034 -0.0840 -2.61 0.068 -0.0805 -1.47 0.158 -0.0738 -0.30 0.275 -0.0721 0.35 0.336 -0.0703 1.64 0.449 -0.0655 2.88 0.560 -0.0624 3.63 0.624 -0.0606 4.97 0.734 -0.0561 5.72 0.793 -0.0538 7.00 0.887 -0.0490 7.71 0.934 -0.0456 8.92 1.002 -0.0396 9.58 1.031 -0.0357 10.74 1.072 -0.0315 11.83 1.100 -0.0304 12.91 1.115 -0.0360 13.97 1.126 -0.0443 14.60 1.130 -0.0494 15.75 1.109 -0.0600 16.92 1.111 -0.0699 17.38 0.985 -0.1028 18.84 0.960 -0.1353 16.96 1.119 -0.0717 15.89 1.127 -0.0601 14.76 1.114 -0.0549 13.73 1.113 -0.0458 12.72 1.107 -0.0377 11.78 1.099 -0.0316 10.83 1.077 -0.0321 9.81 1.045 -0.0361 8.74 0.997 -0.0418 7.62 0.933 -0.0473 6.98 0.890 -0.0499 5.77 0.800 -0.0545 4.52 0.700 -0.0585 3.78 0.636 -0.0606 2.47 0.521 -0.0641 1.67 0.448 -0.0659 0.32 0.333 -0.0705 -0.37 0.268 -0.0721 -1.64 0.142 -0.0742 -2.31 0.088 -0.0782 -3.57 -0.022 -0.0831 -4.75 -0.133 -0.0856 -5.39 -0.196 -0.0854 -6.55 -0.314 -0.0755 Tabulated from data in file PG01756.DAT & reduced using program Q06.01L Average Reynolds #: 402800 Number of angles of attack: 49 alpha / Cl / Cm -6.02 -0.252 -0.0851 -4.50 -0.116 -0.0819 -3.64 -0.039 -0.0792 -2.71 0.035 -0.0748 -1.35 0.162 -0.0717 -0.31 0.262 -0.0693 0.28 0.317 -0.0675 1.90 0.467 -0.0641 2.54 0.525 -0.0625 3.69 0.627 -0.0598 4.94 0.731 -0.0561 5.62 0.786 -0.0540 7.00 0.887 -0.0488 7.74 0.937 -0.0465 9.01 1.007 -0.0391 9.70 1.038 -0.0358 10.86 1.079 -0.0324 11.96 1.110 -0.0345 12.57 1.117 -0.0376 13.63 1.115 -0.0495 14.75 1.123 -0.0543 15.85 1.123 -0.0634 16.91 1.129 -0.0721 18.02 1.129 -0.0762 18.34 1.099 -0.1031 16.94 1.126 -0.0719 15.88 1.120 -0.0606 14.73 1.116 -0.0547 13.74 1.121 -0.0490 12.81 1.117 -0.0423 11.86 1.107 -0.0331 10.89 1.081 -0.0322 9.89 1.045 -0.0351 8.88 0.999 -0.0392 7.76 0.932 -0.0446 6.58 0.851 -0.0494 5.86 0.798 -0.0522 4.43 0.683 -0.0572 3.65 0.618 -0.0594 2.32 0.501 -0.0629 1.66 0.441 -0.0642 0.42 0.324 -0.0670 -0.21 0.266 -0.0688 -1.34 0.157 -0.0719 -2.42 0.055 -0.0739 -3.45 -0.026 -0.0789 -4.45 -0.119 -0.0816 -5.46 -0.208 -0.0841 -6.46 -0.301 -0.0845 Tabulated from data in file PG01758.DAT & reduced using program Q06.01L File CLARKYBT.LFT created on 10-24-1997 at 19:34:41 using program FORMAT :::::::::::::: DH4009.LFT :::::::::::::: Airfoil: DH4009 Builder: D. Stanley Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 101100 Number of angles of attack: 77 alpha / Cl / Cm -4.57 -0.417 0.0042 -3.81 -0.357 0.0057 -3.37 -0.327 0.0085 -2.94 -0.309 0.0172 -2.47 -0.285 0.0265 -1.67 -0.110 0.0124 -1.24 -0.049 0.0061 -0.78 0.000 0.0003 -0.34 0.039 -0.0032 0.43 0.017 0.0114 0.33 0.024 0.0029 1.49 0.154 -0.0014 1.38 0.139 -0.0084 2.58 0.319 -0.0074 2.20 0.294 -0.0213 3.29 0.368 -0.0020 3.71 0.389 0.0032 4.44 0.438 0.0049 4.85 0.470 0.0076 5.25 0.502 0.0088 5.98 0.560 0.0093 6.37 0.597 0.0120 6.80 0.629 0.0124 7.49 0.688 0.0119 7.91 0.718 0.0093 8.33 0.746 0.0004 9.04 0.780 -0.0198 9.41 0.795 -0.0311 9.83 0.797 -0.0413 10.51 0.803 -0.0596 10.91 0.799 -0.0647 11.57 0.765 -0.0730 11.72 0.791 -0.0762 12.41 0.773 -0.0796 12.81 0.768 -0.0810 13.51 0.765 -0.0841 13.90 0.770 -0.0839 14.63 0.770 -0.0857 14.53 0.771 -0.0946 13.89 0.779 -0.0944 13.21 0.785 -0.0966 12.88 0.774 -0.0931 12.24 0.777 -0.0888 11.93 0.786 -0.0857 11.28 0.772 -0.0783 10.97 0.807 -0.0760 10.34 0.789 -0.0634 10.03 0.800 -0.0570 9.42 0.793 -0.0389 8.87 0.776 -0.0233 8.24 0.737 -0.0037 7.95 0.717 0.0027 7.29 0.656 0.0077 6.75 0.613 0.0101 6.32 0.586 0.0104 5.72 0.537 0.0086 5.34 0.511 0.0064 4.75 0.460 0.0056 4.37 0.433 0.0033 3.74 0.388 0.0010 3.08 0.357 -0.0061 2.76 0.335 -0.0114 2.10 0.278 -0.0166 1.74 0.209 -0.0117 1.10 0.099 0.0003 0.75 0.055 0.0044 0.17 0.030 0.0051 -0.41 0.045 -0.0045 -0.77 0.011 -0.0032 -1.36 -0.059 0.0042 -2.00 -0.175 0.0158 -2.32 -0.258 0.0224 -2.91 -0.302 0.0171 -3.48 -0.329 0.0085 -3.83 -0.359 0.0050 -4.41 -0.407 0.0049 -5.02 -0.453 0.0039 Tabulated from data in file CL01089.DAT & reduced using program Q06.01L Average Reynolds #: 201900 Number of angles of attack: 49 alpha / Cl / Cm -6.60 -0.596 -0.0004 -5.47 -0.499 0.0014 -4.36 -0.404 0.0044 -3.26 -0.315 0.0074 -2.46 -0.265 0.0130 -1.36 -0.160 0.0163 -0.30 -0.016 0.0080 0.78 0.113 0.0032 1.99 0.253 -0.0016 2.80 0.344 -0.0034 3.93 0.411 0.0035 5.06 0.502 0.0066 5.82 0.564 0.0089 7.09 0.682 0.0115 7.80 0.741 0.0039 9.09 0.820 -0.0367 10.16 0.826 -0.0643 10.90 0.819 -0.0782 12.05 0.778 -0.0860 13.27 0.762 -0.0867 14.07 0.765 -0.0881 14.89 0.769 -0.0888 16.13 0.770 -0.0896 16.93 0.799 -0.0959 18.17 0.807 -0.0957 16.35 0.772 -0.0929 15.23 0.769 -0.0918 14.14 0.747 -0.0873 13.02 0.757 -0.0879 12.27 0.789 -0.0918 11.24 0.804 -0.0846 10.25 0.832 -0.0675 9.29 0.821 -0.0448 8.40 0.780 -0.0159 7.21 0.693 0.0095 6.34 0.620 0.0097 5.24 0.515 0.0064 4.33 0.440 0.0040 3.02 0.351 -0.0015 2.07 0.261 -0.0029 1.06 0.144 0.0025 0.11 0.027 0.0063 -0.81 -0.088 0.0114 -2.05 -0.236 0.0163 -2.96 -0.295 0.0098 -3.91 -0.369 0.0067 -4.87 -0.451 0.0043 -6.22 -0.566 -0.0004 -7.23 -0.655 -0.0037 Tabulated from data in file CL01083.DAT & reduced using program Q06.01L Average Reynolds #: 302500 Number of angles of attack: 49 alpha / Cl / Cm -6.59 -0.616 -0.0031 -5.37 -0.508 -0.0003 -4.15 -0.399 0.0037 -3.31 -0.327 0.0057 -2.15 -0.218 0.0059 -1.34 -0.112 0.0021 -0.22 0.004 0.0029 1.00 0.105 0.0071 1.80 0.190 0.0080 2.72 0.326 0.0033 3.81 0.426 0.0028 4.92 0.519 0.0063 5.98 0.611 0.0097 7.00 0.700 0.0114 7.90 0.772 0.0014 9.01 0.831 -0.0342 9.98 0.853 -0.0597 10.90 0.830 -0.0798 11.84 0.804 -0.0897 12.82 0.777 -0.0895 14.15 0.765 -0.0885 14.80 0.767 -0.0898 16.17 0.786 -0.0937 17.10 0.795 -0.0951 18.04 0.833 -0.1024 16.31 0.792 -0.0958 15.24 0.778 -0.0937 14.14 0.780 -0.0933 13.06 0.774 -0.0901 12.30 0.785 -0.0913 11.28 0.815 -0.0867 10.31 0.845 -0.0707 9.41 0.842 -0.0480 8.39 0.803 -0.0113 7.35 0.727 0.0093 6.23 0.631 0.0100 5.37 0.555 0.0069 4.14 0.453 0.0034 3.23 0.383 0.0002 2.20 0.243 0.0059 1.05 0.112 0.0073 0.07 0.030 0.0046 -0.85 -0.057 0.0029 -2.10 -0.210 0.0063 -2.99 -0.302 0.0082 -3.95 -0.385 0.0057 -4.95 -0.474 0.0026 -6.01 -0.569 -0.0018 -7.14 -0.665 -0.0056 Tabulated from data in file CL01085.DAT & reduced using program Q06.01L Average Reynolds #: 403100 Number of angles of attack: 46 alpha / Cl / Cm -5.40 -0.535 -0.0012 -4.07 -0.407 0.0035 -3.21 -0.326 0.0053 -2.36 -0.229 0.0025 -1.17 -0.094 0.0016 -0.33 -0.011 0.0031 0.93 0.103 0.0060 1.86 0.219 0.0077 2.92 0.327 0.0074 3.93 0.447 0.0037 4.98 0.539 0.0060 6.01 0.629 0.0096 6.99 0.717 0.0106 8.03 0.805 -0.0078 8.75 0.845 -0.0339 9.80 0.867 -0.0651 10.84 0.844 -0.0828 11.95 0.829 -0.0904 12.96 0.812 -0.0918 14.01 0.797 -0.0914 14.99 0.838 -0.0992 15.93 0.957 -0.1207 16.84 0.960 -0.1133 17.76 0.996 -0.1206 16.21 0.983 -0.1236 15.05 0.868 -0.0925 14.45 0.838 -0.0949 13.52 0.813 -0.0876 12.15 0.874 -0.0925 11.19 0.860 -0.0866 10.32 0.886 -0.0765 9.05 0.865 -0.0423 8.56 0.848 -0.0262 7.27 0.738 0.0084 6.31 0.664 0.0111 5.20 0.563 0.0075 4.32 0.486 0.0052 3.10 0.359 0.0064 2.20 0.270 0.0076 1.26 0.161 0.0066 -0.02 0.024 0.0033 -1.02 -0.075 0.0025 -2.08 -0.197 0.0032 -3.12 -0.315 0.0064 -4.20 -0.416 0.0049 -4.97 -0.489 0.0024 Tabulated from data in file CL01087.DAT & reduced using program Q06.01L Average Reynolds #: 504500 Number of angles of attack: 19 alpha / Cl / Cm -6.64 -0.632 -0.0095 -5.06 -0.491 -0.0036 -4.44 -0.435 -0.0013 -3.15 -0.299 -0.0012 -1.90 -0.163 -0.0026 -1.15 -0.088 -0.0012 0.10 0.033 0.0004 1.23 0.145 0.0020 1.91 0.214 0.0031 3.07 0.323 0.0044 4.03 0.433 0.0014 5.04 0.526 0.0023 6.08 0.615 0.0055 7.12 0.699 0.0098 7.94 0.761 0.0058 9.00 0.826 -0.0274 9.75 0.845 -0.0535 10.34 0.856 -0.0724 11.03 0.875 -0.0795 Tabulated from data in file CL02071.DAT & reduced using program Q06.01L File DH4009.LFT created on 10-24-1997 at 19:34:41 using program FORMAT :::::::::::::: E231.LFT :::::::::::::: Airfoil: E231 Builder: M. Lachowski Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 61100 Number of angles of attack: 49 alpha / Cl / Cm -5.47 -0.472 -0.0096 -4.21 -0.382 -0.0099 -2.96 -0.228 -0.0073 -2.07 -0.183 -0.0036 -1.19 -0.103 -0.0067 -0.06 0.016 -0.0119 1.09 0.105 -0.0146 1.90 0.159 -0.0162 3.06 0.224 -0.0204 3.89 0.288 -0.0245 5.09 0.400 -0.0299 5.94 0.577 -0.0360 7.16 0.775 -0.0303 8.32 0.868 -0.0233 9.17 0.916 -0.0178 10.37 0.974 -0.0105 11.14 1.006 -0.0066 12.26 1.030 -0.0018 13.36 1.025 0.0009 14.04 0.670 -0.0465 15.20 0.680 -0.0641 16.05 0.747 -0.0709 17.21 0.721 -0.0716 18.04 0.769 -0.0779 19.21 0.775 -0.0814 17.25 0.715 -0.0790 16.18 0.712 -0.0802 15.37 0.713 -0.0762 14.27 0.675 -0.0679 13.20 0.662 -0.0636 12.49 0.678 -0.0586 11.51 0.987 -0.0189 10.48 0.965 -0.0153 9.50 0.930 -0.0200 8.48 0.876 -0.0253 7.44 0.807 -0.0335 6.36 0.671 -0.0419 5.25 0.398 -0.0364 4.17 0.319 -0.0312 3.46 0.258 -0.0251 2.39 0.196 -0.0249 1.33 0.109 -0.0235 0.28 0.038 -0.0240 -0.76 -0.056 -0.0204 -1.77 -0.153 -0.0149 -2.80 -0.204 -0.0239 -3.84 -0.343 -0.0143 -4.90 -0.434 -0.0124 -5.98 -0.505 -0.0146 Tabulated from data in file CL01251.DAT & reduced using program Q06.01L Average Reynolds #: 100800 Number of angles of attack: 49 alpha / Cl / Cm -5.44 -0.445 -0.0232 -4.14 -0.347 -0.0216 -2.93 -0.228 -0.0267 -2.07 -0.172 -0.0187 -1.15 0.007 -0.0358 0.04 0.086 -0.0351 0.89 0.127 -0.0327 2.11 0.219 -0.0346 2.98 0.289 -0.0353 4.25 0.485 -0.0399 5.15 0.659 -0.0410 6.03 0.758 -0.0372 7.27 0.864 -0.0316 8.13 0.933 -0.0286 9.33 0.994 -0.0211 10.15 1.028 -0.0165 11.31 1.076 -0.0111 12.12 1.097 -0.0079 13.27 1.106 -0.0042 14.07 1.098 -0.0025 15.14 0.782 -0.0680 16.02 0.794 -0.0756 17.26 0.829 -0.0862 18.17 0.821 -0.0873 19.01 0.822 -0.0910 17.45 0.817 -0.0912 16.29 0.808 -0.0881 15.18 0.798 -0.0820 14.38 0.817 -0.0760 13.30 0.858 -0.0648 12.68 1.106 -0.0131 11.59 1.079 -0.0133 10.57 1.041 -0.0169 9.55 1.001 -0.0224 8.51 0.956 -0.0288 7.43 0.878 -0.0333 6.31 0.781 -0.0387 5.52 0.704 -0.0435 4.34 0.490 -0.0453 3.17 0.306 -0.0402 2.43 0.234 -0.0372 1.31 0.146 -0.0356 0.23 0.087 -0.0387 -0.84 0.038 -0.0431 -1.93 -0.113 -0.0324 -3.01 -0.242 -0.0312 -3.75 -0.304 -0.0289 -4.88 -0.411 -0.0258 -5.99 -0.480 -0.0286 Tabulated from data in file CL01253.DAT & reduced using program Q06.01L Average Reynolds #: 201400 Number of angles of attack: 49 alpha / Cl / Cm -5.45 -0.290 -0.0494 -4.05 -0.190 -0.0480 -3.14 -0.128 -0.0455 -1.81 -0.048 -0.0351 -0.88 0.036 -0.0294 0.13 0.242 -0.0490 1.12 0.362 -0.0536 2.03 0.444 -0.0513 2.93 0.520 -0.0475 4.09 0.632 -0.0428 5.38 0.754 -0.0396 6.27 0.830 -0.0373 7.15 0.892 -0.0335 8.42 0.964 -0.0260 9.25 1.011 -0.0217 10.06 1.057 -0.0180 11.21 1.108 -0.0125 12.37 1.138 -0.0071 13.12 1.140 -0.0057 14.22 1.125 -0.0119 15.04 1.112 -0.0172 16.23 1.080 -0.0247 16.87 0.884 -0.0995 18.29 0.865 -0.1025 19.22 0.876 -0.1030 17.41 0.871 -0.1031 16.46 0.880 -0.1000 15.15 0.903 -0.0925 14.49 1.120 -0.0166 13.41 1.138 -0.0070 12.37 1.139 -0.0089 11.69 1.122 -0.0114 10.62 1.085 -0.0161 9.57 1.030 -0.0207 8.51 0.970 -0.0258 7.40 0.907 -0.0325 6.26 0.830 -0.0378 5.48 0.762 -0.0400 4.26 0.651 -0.0430 3.25 0.548 -0.0474 2.08 0.450 -0.0527 1.26 0.378 -0.0554 0.07 0.226 -0.0483 -0.82 0.050 -0.0312 -2.04 -0.064 -0.0383 -2.86 -0.112 -0.0455 -4.06 -0.191 -0.0499 -4.91 -0.252 -0.0518 -6.18 -0.345 -0.0539 Tabulated from data in file CL01257.DAT & reduced using program Q06.01L Average Reynolds #: 301500 Number of angles of attack: 49 alpha / Cl / Cm -5.52 -0.346 -0.0438 -4.04 -0.230 -0.0383 -3.04 -0.144 -0.0371 -2.02 -0.075 -0.0318 -1.04 0.002 -0.0254 -0.06 0.093 -0.0202 0.92 0.248 -0.0310 2.04 0.433 -0.0401 3.07 0.548 -0.0420 4.01 0.641 -0.0411 5.39 0.775 -0.0399 6.33 0.853 -0.0375 7.25 0.913 -0.0325 8.15 0.958 -0.0258 9.44 1.038 -0.0199 10.26 1.086 -0.0164 11.07 1.128 -0.0129 12.24 1.153 -0.0071 13.42 1.148 -0.0065 14.24 1.131 -0.0106 15.41 1.106 -0.0241 16.28 1.082 -0.0321 17.17 1.048 -0.0401 18.11 0.906 -0.1039 19.32 0.891 -0.1086 17.08 0.961 -0.0958 16.14 1.006 -0.0887 15.50 1.106 -0.0268 14.36 1.133 -0.0146 13.36 1.152 -0.0081 12.40 1.157 -0.0066 11.36 1.132 -0.0100 10.36 1.088 -0.0142 9.69 1.052 -0.0173 8.23 0.959 -0.0231 7.52 0.921 -0.0285 6.30 0.847 -0.0359 5.49 0.778 -0.0383 4.15 0.650 -0.0398 3.26 0.560 -0.0403 2.39 0.468 -0.0396 1.12 0.301 -0.0328 0.08 0.102 -0.0197 -0.87 0.010 -0.0227 -1.73 -0.059 -0.0286 -3.08 -0.151 -0.0365 -4.06 -0.235 -0.0383 -5.00 -0.316 -0.0396 -5.97 -0.395 -0.0418 Tabulated from data in file CL01259.DAT & reduced using program Q06.01L Average Reynolds #: 402800 Number of angles of attack: 49 alpha / Cl / Cm -5.47 -0.380 -0.0326 -4.00 -0.247 -0.0319 -3.21 -0.173 -0.0312 -2.04 -0.075 -0.0291 -1.13 -0.006 -0.0248 0.39 0.131 -0.0182 1.04 0.231 -0.0176 1.91 0.341 -0.0207 3.12 0.497 -0.0267 4.03 0.618 -0.0323 5.38 0.780 -0.0381 6.29 0.861 -0.0373 7.24 0.916 -0.0315 8.09 0.956 -0.0245 9.23 1.033 -0.0202 10.35 1.104 -0.0162 11.10 1.131 -0.0121 12.19 1.157 -0.0075 13.19 1.168 -0.0087 14.22 1.150 -0.0156 15.23 1.120 -0.0303 16.44 1.081 -0.0413 17.27 1.051 -0.0507 17.67 0.967 -0.1038 19.09 0.917 -0.1130 17.41 1.021 -0.1022 16.62 1.060 -0.0471 15.60 1.106 -0.0363 14.64 1.133 -0.0195 13.51 1.162 -0.0123 12.68 1.163 -0.0070 11.61 1.140 -0.0074 10.68 1.113 -0.0117 9.48 1.050 -0.0165 8.53 0.982 -0.0194 7.50 0.924 -0.0254 6.38 0.865 -0.0341 5.55 0.794 -0.0356 4.37 0.663 -0.0328 3.22 0.513 -0.0264 2.42 0.411 -0.0230 1.39 0.273 -0.0178 0.42 0.132 -0.0172 -1.04 0.001 -0.0239 -2.04 -0.079 -0.0289 -2.95 -0.156 -0.0307 -3.89 -0.243 -0.0315 -5.16 -0.358 -0.0332 -5.97 -0.428 -0.0341 Tabulated from data in file CL01261.DAT & reduced using program Q06.01L File E231.LFT created on 10-24-1997 at 19:34:41 using program FORMAT :::::::::::::: E374B.LFT :::::::::::::: Airfoil: E374 (B) Builder: M. Bame Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60800 Number of angles of attack: 49 alpha / Cl / Cm -6.35 -0.391 -0.0433 -5.17 -0.345 -0.0399 -4.23 -0.306 -0.0361 -2.94 -0.216 -0.0241 -1.94 -0.127 -0.0243 -0.92 -0.034 -0.0283 0.13 0.125 -0.0413 1.16 0.243 -0.0507 2.20 0.327 -0.0557 2.91 0.355 -0.0558 4.00 0.456 -0.0593 5.06 0.554 -0.0627 6.15 0.767 -0.0605 7.21 0.894 -0.0492 8.29 0.970 -0.0381 9.33 0.998 -0.0284 10.07 1.024 -0.0236 11.26 1.063 -0.0195 12.19 1.071 -0.0183 13.09 1.061 -0.0257 14.22 1.014 -0.0696 15.19 0.939 -0.1002 16.15 0.943 -0.1112 17.17 0.952 -0.1205 18.15 0.904 -0.1161 16.82 0.961 -0.1268 15.74 0.965 -0.1167 14.67 0.958 -0.1065 13.68 1.064 -0.0701 12.69 1.078 -0.0217 11.73 1.082 -0.0190 10.71 1.058 -0.0214 9.70 1.024 -0.0263 8.67 1.003 -0.0340 7.69 0.961 -0.0457 6.80 0.879 -0.0539 5.66 0.651 -0.0623 4.54 0.526 -0.0576 3.68 0.447 -0.0547 2.64 0.398 -0.0590 1.60 0.307 -0.0609 0.56 0.203 -0.0606 -0.54 0.058 -0.0496 -1.54 -0.064 -0.0373 -2.53 -0.151 -0.0339 -3.53 -0.238 -0.0248 -4.54 -0.297 -0.0249 -5.55 -0.342 -0.0315 -6.56 -0.385 -0.0355 Tabulated from data in file CL01012.DAT & reduced using program Q06.01L Average Reynolds #: 100600 Number of angles of attack: 49 alpha / Cl / Cm -6.36 -0.446 -0.0265 -5.20 -0.389 -0.0281 -4.02 -0.254 -0.0351 -3.16 -0.130 -0.0429 -1.99 0.036 -0.0526 -1.09 0.150 -0.0599 0.10 0.255 -0.0618 0.96 0.313 -0.0598 2.16 0.389 -0.0584 3.07 0.452 -0.0570 4.45 0.592 -0.0518 5.07 0.656 -0.0471 6.46 0.797 -0.0417 7.05 0.848 -0.0402 8.25 0.906 -0.0327 9.08 0.943 -0.0276 10.24 0.990 -0.0229 11.52 1.013 -0.0201 12.28 1.017 -0.0251 13.42 1.033 -0.0739 14.14 0.904 -0.1001 15.20 0.845 -0.1127 16.29 0.847 -0.1160 17.15 0.864 -0.1216 18.24 0.860 -0.1220 16.54 0.841 -0.1214 15.53 0.867 -0.1205 14.52 0.856 -0.1104 13.57 0.996 -0.0950 12.64 1.033 -0.0482 11.78 1.024 -0.0196 10.65 1.008 -0.0217 9.75 0.979 -0.0254 8.58 0.930 -0.0304 7.61 0.892 -0.0377 6.64 0.826 -0.0429 5.66 0.727 -0.0479 4.64 0.621 -0.0535 3.63 0.512 -0.0577 2.42 0.414 -0.0587 1.43 0.347 -0.0603 0.49 0.289 -0.0636 -0.45 0.221 -0.0664 -1.59 0.099 -0.0600 -2.54 -0.029 -0.0509 -3.69 -0.203 -0.0390 -4.64 -0.320 -0.0274 -5.58 -0.401 -0.0259 -6.70 -0.453 -0.0329 Tabulated from data in file CL01014.DAT & reduced using program Q06.01L Average Reynolds #: 201400 Number of angles of attack: 49 alpha / Cl / Cm -6.91 -0.478 -0.0329 -5.16 -0.288 -0.0458 -3.93 -0.150 -0.0523 -3.01 -0.078 -0.0484 -2.10 -0.011 -0.0410 -0.89 0.106 -0.0390 0.03 0.257 -0.0518 1.03 0.340 -0.0506 2.47 0.473 -0.0480 3.08 0.530 -0.0471 4.50 0.669 -0.0451 5.19 0.753 -0.0436 6.50 0.875 -0.0405 7.45 0.923 -0.0343 8.26 0.958 -0.0290 9.44 1.008 -0.0225 10.19 1.033 -0.0187 11.24 1.051 -0.0153 12.27 1.096 -0.0206 13.20 1.105 -0.0649 14.26 1.062 -0.1097 15.58 0.937 -0.1182 16.25 0.943 -0.1203 17.63 0.941 -0.1241 18.28 0.936 -0.1248 16.50 0.953 -0.1241 15.63 0.950 -0.1210 14.52 1.040 -0.1127 13.76 1.087 -0.0931 12.79 1.105 -0.0529 11.68 1.066 -0.0156 10.62 1.050 -0.0176 9.76 1.032 -0.0213 8.67 0.994 -0.0271 7.74 0.954 -0.0327 6.58 0.901 -0.0406 5.59 0.813 -0.0432 4.68 0.708 -0.0446 3.67 0.612 -0.0455 2.64 0.507 -0.0463 1.61 0.418 -0.0474 0.56 0.295 -0.0490 -0.61 0.146 -0.0405 -1.63 0.029 -0.0385 -2.67 -0.062 -0.0436 -3.79 -0.147 -0.0501 -4.64 -0.228 -0.0495 -5.75 -0.381 -0.0361 -6.88 -0.476 -0.0338 Tabulated from data in file CL01016.DAT & reduced using program Q06.01L Average Reynolds #: 302100 Number of angles of attack: 49 alpha / Cl / Cm -6.10 -0.394 -0.0435 -5.26 -0.291 -0.0496 -4.09 -0.187 -0.0466 -3.15 -0.104 -0.0451 -1.53 0.036 -0.0380 -1.10 0.075 -0.0361 -0.00 0.192 -0.0368 1.04 0.370 -0.0466 2.07 0.473 -0.0454 3.07 0.571 -0.0445 4.52 0.715 -0.0435 5.21 0.784 -0.0428 6.14 0.867 -0.0409 7.43 0.939 -0.0336 8.27 0.983 -0.0287 9.43 1.036 -0.0226 10.22 1.059 -0.0187 11.15 1.087 -0.0159 12.39 1.171 -0.0362 13.27 1.164 -0.0632 14.20 1.126 -0.1019 15.26 1.025 -0.1167 16.16 0.982 -0.1223 17.25 0.986 -0.1252 18.10 0.984 -0.1265 16.69 0.988 -0.1242 15.56 1.010 -0.1201 14.44 1.122 -0.1080 13.69 1.141 -0.0845 12.76 1.151 -0.0500 11.78 1.152 -0.0174 10.65 1.071 -0.0153 9.66 1.045 -0.0192 8.60 1.001 -0.0248 7.71 0.953 -0.0301 6.49 0.892 -0.0375 5.70 0.827 -0.0404 4.62 0.722 -0.0423 3.50 0.609 -0.0436 2.24 0.487 -0.0456 1.61 0.425 -0.0465 0.52 0.287 -0.0452 -0.63 0.110 -0.0343 -1.67 0.024 -0.0382 -2.63 -0.057 -0.0429 -4.18 -0.195 -0.0459 -4.60 -0.231 -0.0475 -6.16 -0.399 -0.0431 -7.03 -0.497 -0.0387 Tabulated from data in file CL01018.DAT & reduced using program Q06.01L File E374B.LFT created on 10-24-1997 at 19:34:41 using program FORMAT :::::::::::::: E387C.LFT :::::::::::::: Airfoil: E387 (C) Builder: J. Robertson Comment: clean (used for validating UIUC data against LTPT data) Number of Reynolds #'s: 5 Average Reynolds #: 60043 Number of angles of attack: 49 alpha / Cl / Cm -6.13 -0.337 -0.0253 -5.12 -0.257 -0.0572 -4.09 -0.178 -0.0649 -3.08 -0.097 -0.0711 -2.11 0.026 -0.0806 -0.98 0.160 -0.0899 0.00 0.258 -0.0950 0.96 0.377 -0.1003 2.04 0.484 -0.1098 3.00 0.538 -0.1118 4.24 0.597 -0.1135 5.15 0.649 -0.1150 6.01 0.695 -0.1161 7.07 0.753 -0.1181 8.17 1.031 -0.0931 9.26 1.154 -0.0817 10.21 1.203 -0.0754 11.20 1.208 -0.0672 12.23 1.233 -0.0625 13.37 1.231 -0.0622 14.18 1.203 -0.0888 15.26 1.027 -0.1248 16.15 1.035 -0.1711 17.22 1.076 -0.1782 18.11 1.079 -0.1864 17.58 1.082 -0.1944 16.58 1.052 -0.1770 15.61 1.071 -0.1723 14.62 1.192 -0.1328 13.64 1.227 -0.0642 12.79 1.213 -0.0619 11.63 1.208 -0.0650 10.71 1.195 -0.0714 9.76 1.203 -0.0777 8.62 1.150 -0.0902 7.43 0.786 -0.1194 6.46 0.726 -0.1182 5.56 0.682 -0.1178 4.53 0.628 -0.1144 3.48 0.571 -0.1134 2.47 0.526 -0.1182 1.52 0.453 -0.1200 0.44 0.347 -0.1132 -0.64 0.230 -0.1006 -1.58 0.131 -0.0935 -2.57 -0.004 -0.0786 -3.66 -0.145 -0.0646 -4.61 -0.225 -0.0624 -5.62 -0.315 -0.0441 Tabulated from data in file cl02129.dat & reduced using program C06.01 Average Reynolds #: 99865 Number of angles of attack: 49 alpha / Cl / Cm -6.08 -0.347 -0.0128 -5.09 -0.291 -0.0436 -4.11 -0.134 -0.0767 -2.99 0.028 -0.0938 -2.03 0.154 -0.1035 -0.99 0.246 -0.1018 -0.01 0.332 -0.1033 0.98 0.423 -0.1033 2.00 0.504 -0.1028 3.06 0.599 -0.1022 4.13 0.699 -0.1006 5.15 0.796 -0.0942 6.12 0.900 -0.0898 7.15 1.004 -0.0856 8.24 1.110 -0.0837 9.30 1.175 -0.0772 10.26 1.173 -0.0699 11.75 1.212 -0.0624 12.24 1.209 -0.0619 13.33 1.203 -0.0627 14.23 1.176 -0.0699 15.17 1.093 -0.1687 16.18 1.068 -0.1772 17.16 1.060 -0.1809 18.42 1.052 -0.1846 17.47 1.062 -0.1943 16.45 1.077 -0.1868 15.58 1.033 -0.1852 14.57 1.146 -0.1631 13.71 1.190 -0.0696 12.68 1.203 -0.0651 11.74 1.204 -0.0653 10.60 1.193 -0.0698 9.60 1.184 -0.0777 8.71 1.160 -0.0847 7.64 1.080 -0.0879 6.64 0.988 -0.0905 5.60 0.882 -0.0950 4.53 0.771 -0.1006 3.57 0.675 -0.1044 2.53 0.584 -0.1044 1.45 0.482 -0.1041 0.45 0.398 -0.1046 -0.56 0.307 -0.1044 -1.58 0.204 -0.1045 -2.57 0.100 -0.1014 -3.63 -0.049 -0.0854 -4.70 -0.204 -0.0644 -5.61 -0.319 -0.0269 Tabulated from data in file cl02131.dat & reduced using program C06.01 Average Reynolds #: 199970 Number of angles of attack: 49 alpha / Cl / Cm -6.13 -0.381 -0.0207 -5.00 -0.178 -0.0800 -3.95 -0.047 -0.0887 -2.97 0.042 -0.0875 -1.99 0.142 -0.0874 -0.92 0.243 -0.0862 0.12 0.344 -0.0874 1.03 0.448 -0.0881 2.10 0.556 -0.0888 3.29 0.683 -0.0899 4.42 0.798 -0.0891 5.15 0.871 -0.0889 6.22 0.975 -0.0879 7.20 1.079 -0.0865 8.24 1.155 -0.0821 9.28 1.198 -0.0750 10.30 1.211 -0.0676 11.25 1.216 -0.0630 12.29 1.212 -0.0630 13.28 1.215 -0.0669 14.23 1.206 -0.0727 15.05 1.137 -0.1468 16.07 1.070 -0.1833 17.10 1.053 -0.1849 18.19 1.089 -0.1878 17.55 1.065 -0.1865 16.49 1.082 -0.1898 15.41 1.210 -0.1625 14.61 1.256 -0.1192 13.69 1.211 -0.0674 12.69 1.215 -0.0629 11.78 1.217 -0.0623 10.73 1.217 -0.0632 9.73 1.205 -0.0692 8.58 1.174 -0.0773 7.47 1.104 -0.0822 6.62 1.027 -0.0841 5.58 0.923 -0.0849 4.55 0.815 -0.0852 3.57 0.713 -0.0851 2.52 0.603 -0.0849 1.51 0.491 -0.0844 0.24 0.356 -0.0834 -0.61 0.269 -0.0830 -1.61 0.171 -0.0844 -2.69 0.070 -0.0841 -3.86 -0.035 -0.0856 -4.84 -0.150 -0.0835 -5.68 -0.303 -0.0502 Tabulated from data in file cl02133.dat & reduced using program C06.01 Average Reynolds #: 299917 Number of angles of attack: 49 alpha / Cl / Cm -6.09 -0.338 -0.0423 -5.18 -0.205 -0.0758 -4.10 -0.076 -0.0835 -3.00 0.031 -0.0838 -1.98 0.139 -0.0842 -0.99 0.244 -0.0860 0.09 0.351 -0.0847 1.02 0.457 -0.0857 2.06 0.566 -0.0868 3.10 0.678 -0.0875 4.14 0.789 -0.0883 5.14 0.896 -0.0882 6.28 1.011 -0.0877 7.25 1.109 -0.0863 8.31 1.178 -0.0814 9.41 1.218 -0.0736 10.28 1.238 -0.0677 11.31 1.242 -0.0635 12.59 1.245 -0.0657 13.28 1.244 -0.0690 14.25 1.319 -0.1113 14.90 1.298 -0.1363 16.04 1.306 -0.1728 17.04 1.277 -0.1792 17.97 1.051 -0.1909 17.63 1.054 -0.1858 16.65 1.225 -0.1795 15.71 1.175 -0.1623 15.04 1.332 -0.1454 13.67 1.249 -0.0704 12.65 1.245 -0.0658 11.73 1.244 -0.0624 10.73 1.244 -0.0627 9.77 1.236 -0.0684 8.68 1.204 -0.0765 7.69 1.148 -0.0815 6.51 1.045 -0.0843 5.46 0.935 -0.0844 4.52 0.835 -0.0849 3.39 0.715 -0.0852 2.52 0.622 -0.0853 1.54 0.508 -0.0848 0.48 0.395 -0.0841 -0.51 0.288 -0.0831 -1.59 0.177 -0.0836 -2.57 0.077 -0.0824 -3.73 -0.041 -0.0814 -4.68 -0.142 -0.0816 -5.63 -0.262 -0.0643 Tabulated from data in file cl02135.dat & reduced using program C06.01 Average Reynolds #: 459546 Number of angles of attack: 49 alpha / Cl / Cm -6.17 -0.344 -0.0411 -5.17 -0.208 -0.0741 -4.09 -0.077 -0.0803 -3.01 0.032 -0.0808 -2.00 0.140 -0.0818 -1.04 0.245 -0.0838 0.06 0.355 -0.0829 1.00 0.462 -0.0839 2.12 0.586 -0.0844 3.20 0.702 -0.0854 4.14 0.803 -0.0857 5.17 0.917 -0.0859 6.20 1.021 -0.0853 7.16 1.111 -0.0836 8.27 1.183 -0.0790 9.33 1.239 -0.0737 10.41 1.269 -0.0683 11.55 1.278 -0.0702 12.43 1.275 -0.0749 13.49 1.272 -0.0815 14.23 1.259 -0.0866 14.59 1.289 -0.1122 15.86 1.222 -0.1627 16.93 1.181 -0.1876 16.81 1.250 -0.1818 17.10 1.192 -0.1895 16.90 1.174 -0.1872 15.92 1.213 -0.1733 15.34 1.273 -0.1424 13.57 1.257 -0.0821 12.46 1.271 -0.0758 11.59 1.269 -0.0710 10.62 1.266 -0.0674 9.59 1.249 -0.0716 8.35 1.185 -0.0767 7.53 1.140 -0.0807 6.44 1.051 -0.0838 5.52 0.956 -0.0846 4.26 0.822 -0.0852 3.63 0.752 -0.0839 2.56 0.639 -0.0838 1.55 0.522 -0.0831 0.48 0.404 -0.0824 -0.67 0.286 -0.0834 -1.54 0.190 -0.0821 -2.54 0.083 -0.0813 -3.61 -0.032 -0.0801 -4.67 -0.145 -0.0799 -5.61 -0.266 -0.0634 Tabulated from data in file cl02137.dat & reduced using program C06.01 File e387c.lft created using program C06.01 on Mon Feb 02 15:11:35 1998 :::::::::::::: E387D.LFT :::::::::::::: Airfoil: E387 (D) Builder: Y. Tinel Comment: clean (6" chord) Number of Reynolds #'s: 2 Average Reynolds #: 60019 Number of angles of attack: 53 alpha / Cl / Cm -7.26 -0.392 0.0320 -6.24 -0.381 0.0114 -5.18 -0.346 -0.0181 -4.08 -0.271 -0.0537 -2.88 -0.146 -0.0670 -2.06 -0.043 -0.0742 -0.98 0.118 -0.0846 0.08 0.252 -0.0885 1.17 0.382 -0.0991 2.43 0.489 -0.1017 2.93 0.519 -0.1023 3.98 0.599 -0.1042 5.00 0.662 -0.1063 5.99 0.757 -0.1032 7.03 0.976 -0.0925 8.08 1.072 -0.0790 9.14 1.164 -0.0699 10.19 1.194 -0.0591 11.01 1.215 -0.0538 12.03 1.233 -0.0493 13.11 1.231 -0.0483 13.80 1.058 -0.1080 15.25 0.983 -0.1325 16.07 0.979 -0.1425 16.91 1.045 -0.1575 18.07 1.015 -0.1605 19.12 0.982 -0.1513 17.81 1.007 -0.1642 17.11 0.981 -0.1647 15.95 0.974 -0.1536 15.09 0.994 -0.1476 14.19 1.025 -0.1321 13.20 1.226 -0.0607 11.94 1.236 -0.0598 11.23 1.221 -0.0627 10.08 1.190 -0.0705 9.13 1.170 -0.0788 8.12 1.086 -0.0880 7.14 0.992 -0.1026 6.19 0.827 -0.1176 5.08 0.669 -0.1143 4.11 0.613 -0.1142 3.18 0.542 -0.1119 2.17 0.472 -0.1133 1.12 0.381 -0.1122 0.15 0.268 -0.1043 -0.83 0.129 -0.0929 -1.82 -0.007 -0.0809 -2.81 -0.136 -0.0705 -3.93 -0.253 -0.0575 -4.88 -0.337 -0.0330 -5.82 -0.374 -0.0076 -6.90 -0.383 0.0162 Tabulated from data in file cl02706.dat & reduced using program C06.01 Average Reynolds #: 199878 Number of angles of attack: 31 alpha / Cl / Cm -7.16 -0.457 0.0382 -6.16 -0.444 0.0200 -5.14 -0.373 -0.0222 -3.97 -0.126 -0.0884 -3.08 -0.034 -0.0885 -1.03 0.169 -0.0878 1.10 0.416 -0.0874 2.97 0.639 -0.0888 5.00 0.867 -0.0899 6.97 1.083 -0.0886 9.08 1.206 -0.0789 11.58 1.243 -0.0663 13.17 1.233 -0.0661 14.66 1.109 -0.1491 16.83 0.972 -0.1674 18.89 0.975 -0.1689 9.14 1.164 -0.0699 10.19 1.194 -0.0591 11.01 1.215 -0.0538 12.03 1.233 -0.0493 13.11 1.231 -0.0483 13.80 1.058 -0.1080 15.25 0.983 -0.1325 16.07 0.979 -0.1425 16.91 1.045 -0.1575 18.07 1.015 -0.1605 19.12 0.982 -0.1513 18.09 0.965 -0.1728 17.09 0.972 -0.1731 16.10 0.972 -0.1652 15.03 1.046 -0.1595 Tabulated from data in file cl02708.dat & reduced using program C06.01 File e387d.lft created using program C06.01 on Mon Feb 02 15:11:35 1998 :::::::::::::: E472.LFT :::::::::::::: Airfoil: E472 Builder: D. Stanley Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 101000 Number of angles of attack: 49 alpha / Cl / Cm -5.95 -0.593 -0.0038 -4.71 -0.476 -0.0028 -3.44 -0.353 0.0000 -2.53 -0.265 0.0021 -1.59 -0.185 0.0048 -0.66 -0.092 0.0055 0.62 0.093 -0.0024 1.57 0.205 -0.0066 2.53 0.290 -0.0050 3.49 0.378 -0.0031 4.48 0.465 -0.0011 5.78 0.575 0.0009 6.73 0.660 0.0020 7.67 0.738 0.0035 8.56 0.707 -0.0426 9.75 0.681 -0.0705 10.66 0.651 -0.0741 11.60 0.643 -0.0769 12.55 0.664 -0.0805 13.50 0.674 -0.0816 14.80 0.688 -0.0848 15.77 0.710 -0.0876 16.77 0.754 -0.0943 17.76 0.773 -0.0979 18.75 0.815 -0.1068 16.99 0.763 -0.1027 16.08 0.720 -0.0961 15.18 0.751 -0.1022 14.02 0.719 -0.0956 13.13 0.660 -0.0865 12.00 0.649 -0.0859 10.86 0.645 -0.0826 10.05 0.656 -0.0781 8.95 0.666 -0.0656 8.19 0.755 -0.0155 7.12 0.698 -0.0015 6.01 0.606 -0.0020 4.90 0.507 -0.0033 4.06 0.435 -0.0043 2.93 0.338 -0.0061 1.82 0.236 -0.0080 1.01 0.164 -0.0115 -0.10 -0.018 -0.0028 -1.20 -0.151 0.0065 -2.29 -0.238 0.0032 -3.10 -0.311 0.0009 -4.20 -0.421 -0.0008 -5.32 -0.527 -0.0029 -6.45 -0.635 -0.0044 Tabulated from data in file CL01073.DAT & reduced using program Q06.01L Average Reynolds #: 202200 Number of angles of attack: 49 alpha / Cl / Cm -5.99 -0.612 -0.0040 -4.66 -0.488 -0.0031 -3.65 -0.393 -0.0010 -2.64 -0.302 0.0012 -1.64 -0.152 -0.0061 -0.60 -0.030 -0.0088 0.43 0.050 -0.0033 1.42 0.146 -0.0010 2.39 0.280 -0.0069 3.75 0.412 -0.0053 4.43 0.475 -0.0037 5.70 0.598 -0.0007 6.68 0.688 0.0014 7.64 0.771 0.0032 8.57 0.854 0.0056 9.77 0.952 0.0085 10.67 1.022 0.0109 11.58 1.083 0.0135 12.34 0.680 -0.0915 13.63 0.695 -0.0925 14.63 0.708 -0.0939 15.64 0.716 -0.0948 16.66 0.742 -0.0989 17.65 0.755 -0.1005 18.62 0.773 -0.1022 17.03 0.754 -0.1034 16.03 0.727 -0.0989 15.04 0.711 -0.0974 14.05 0.689 -0.0939 13.07 0.681 -0.0929 11.79 0.675 -0.0933 10.88 0.681 -0.0903 9.94 0.694 -0.0845 9.06 0.724 -0.0682 7.99 0.802 0.0030 7.18 0.726 0.0013 6.07 0.628 -0.0011 4.95 0.523 -0.0025 4.10 0.443 -0.0046 2.93 0.334 -0.0069 2.05 0.236 -0.0054 0.92 0.092 -0.0006 -0.21 0.004 -0.0066 -1.08 -0.087 -0.0077 -2.22 -0.247 -0.0003 -3.36 -0.369 0.0012 -4.23 -0.449 -0.0004 -5.46 -0.562 -0.0029 -6.37 -0.641 -0.0045 Tabulated from data in file CL01075.DAT & reduced using program Q06.01L Average Reynolds #: 303100 Number of angles of attack: 49 alpha / Cl / Cm -5.99 -0.626 -0.0050 -4.55 -0.492 -0.0032 -3.47 -0.386 -0.0007 -2.42 -0.256 -0.0036 -1.74 -0.156 -0.0089 -0.31 -0.009 -0.0067 0.38 0.054 -0.0050 1.39 0.145 -0.0009 2.38 0.272 -0.0033 3.70 0.424 -0.0057 4.71 0.518 -0.0035 5.68 0.609 -0.0011 6.61 0.697 0.0006 7.52 0.780 0.0024 8.63 0.886 0.0044 9.73 0.988 0.0067 10.59 1.063 0.0088 11.68 1.147 0.0120 12.75 1.212 0.0155 13.82 1.250 0.0183 14.02 0.770 -0.1016 15.49 0.767 -0.1017 16.74 0.765 -0.0983 17.65 0.794 -0.1026 18.58 0.825 -0.1073 16.83 0.777 -0.1000 15.93 0.793 -0.1024 15.04 0.794 -0.1039 14.20 0.763 -0.1001 13.04 0.759 -0.0995 11.93 0.746 -0.0981 11.12 0.733 -0.0916 10.09 0.801 -0.0751 9.36 0.953 0.0048 8.19 0.845 0.0037 6.95 0.729 0.0013 5.94 0.631 -0.0012 4.87 0.531 -0.0037 4.06 0.458 -0.0055 2.91 0.348 -0.0077 1.82 0.196 -0.0004 0.99 0.112 -0.0026 -0.17 0.002 -0.0063 -1.09 -0.077 -0.0097 -2.28 -0.237 -0.0042 -3.17 -0.356 0.0006 -4.40 -0.472 -0.0019 -5.37 -0.570 -0.0040 -6.38 -0.657 -0.0062 Tabulated from data in file CL01077.DAT & reduced using program Q06.01L Average Reynolds #: 403500 Number of angles of attack: 46 alpha / Cl / Cm -4.72 -0.541 -0.0041 -3.71 -0.428 -0.0017 -2.68 -0.278 -0.0076 -1.64 -0.149 -0.0104 -0.44 -0.035 -0.0065 0.66 0.078 -0.0042 1.71 0.178 -0.0014 2.75 0.297 -0.0004 3.71 0.419 -0.0057 4.69 0.517 -0.0038 5.63 0.609 -0.0019 6.54 0.702 -0.0001 7.68 0.812 0.0016 8.52 0.893 0.0031 9.82 1.015 0.0061 10.60 1.082 0.0079 11.61 1.161 0.0107 12.79 1.236 0.0139 13.71 1.272 0.0165 14.56 1.262 -0.0090 14.80 0.806 -0.1003 16.55 0.838 -0.1048 17.52 0.847 -0.1047 18.51 0.899 -0.1083 17.09 0.875 -0.1070 16.12 0.845 -0.1031 14.91 0.822 -0.1007 14.17 0.809 -0.0990 13.00 0.775 -0.0951 12.06 0.794 -0.0929 11.24 0.851 -0.0823 10.86 1.102 0.0078 9.12 0.948 0.0063 8.23 0.868 0.0042 7.07 0.759 0.0023 5.97 0.644 -0.0001 5.03 0.561 -0.0022 4.01 0.463 -0.0047 2.99 0.332 -0.0021 1.92 0.208 -0.0005 0.78 0.099 -0.0037 -0.09 0.009 -0.0054 -1.04 -0.076 -0.0075 -2.38 -0.226 -0.0090 -3.33 -0.366 -0.0014 -4.32 -0.472 -0.0014 Tabulated from data in file CL01079.DAT & reduced using program Q06.01L Average Reynolds #: 504600 Number of angles of attack: 51 alpha / Cl / Cm -5.82 -0.646 -0.0071 -4.66 -0.535 -0.0050 -3.48 -0.406 -0.0045 -2.32 -0.248 -0.0099 -1.57 -0.168 -0.0088 -0.08 -0.022 -0.0051 0.78 0.061 -0.0035 1.60 0.144 -0.0021 3.01 0.278 0.0018 3.70 0.368 -0.0008 4.98 0.517 -0.0032 5.69 0.586 -0.0018 6.91 0.704 0.0008 8.07 0.818 0.0031 8.74 0.883 0.0045 9.83 0.989 0.0067 10.92 1.088 0.0094 12.01 1.179 0.0123 13.03 1.249 0.0154 13.99 1.297 0.0185 14.64 1.292 -0.0001 15.78 1.267 -0.0271 16.85 1.254 -0.0386 17.86 1.234 -0.0512 19.60 0.958 -0.1277 20.55 1.012 -0.1331 18.85 0.914 -0.1231 18.04 0.904 -0.1220 16.86 0.850 -0.1140 16.16 0.817 -0.1039 14.80 0.780 -0.1016 14.00 0.756 -0.0970 13.11 0.757 -0.0952 11.98 0.817 -0.0899 10.11 1.017 0.0081 8.95 0.904 0.0061 8.11 0.822 0.0038 6.72 0.687 0.0007 5.74 0.591 -0.0014 4.64 0.486 -0.0041 4.00 0.408 -0.0027 2.83 0.259 0.0013 1.52 0.135 -0.0027 0.76 0.057 -0.0039 -0.64 -0.084 -0.0062 -1.59 -0.178 -0.0089 -2.45 -0.272 -0.0095 -3.79 -0.457 -0.0020 -4.59 -0.538 -0.0032 -5.51 -0.626 -0.0047 -6.98 -0.764 -0.0073 Tabulated from data in file CL01855.DAT & reduced using program Q06.01L File E472.LFT created on 10-24-1997 at 19:34:41 using program FORMAT :::::::::::::: ESA.LFT :::::::::::::: Airfoil: ESA Builder: B. Halkett Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 101000 Number of angles of attack: 49 alpha / Cl / Cm -5.55 -0.546 0.0243 -4.20 -0.422 0.0227 -3.48 -0.346 0.0200 -2.16 -0.218 0.0205 -1.12 -0.083 0.0207 -0.10 0.010 0.0205 0.92 0.091 0.0259 1.94 0.171 0.0303 2.99 0.259 0.0317 3.72 0.323 0.0321 4.84 0.424 0.0314 5.93 0.537 0.0303 6.95 0.648 0.0290 7.97 0.741 0.0272 8.98 0.831 0.0252 9.96 0.909 0.0216 10.82 0.682 -0.0586 12.12 0.697 -0.0673 12.82 0.717 -0.0715 14.17 0.717 -0.0721 14.88 0.710 -0.0704 15.92 0.740 -0.0773 16.96 0.765 -0.0811 18.02 0.801 -0.0892 19.05 0.776 -0.0837 17.17 0.776 -0.0927 16.23 0.777 -0.0921 15.31 0.731 -0.0831 14.41 0.713 -0.0814 13.19 0.715 -0.0803 12.33 0.687 -0.0723 11.17 0.687 -0.0688 10.32 0.692 -0.0636 9.22 0.828 0.0148 8.43 0.777 0.0239 7.26 0.673 0.0269 6.40 0.589 0.0277 5.20 0.458 0.0308 4.33 0.369 0.0317 3.14 0.263 0.0341 2.28 0.195 0.0326 1.02 0.101 0.0292 0.19 0.037 0.0224 -0.97 -0.064 0.0205 -1.82 -0.197 0.0236 -2.96 -0.291 0.0178 -4.11 -0.415 0.0237 -4.95 -0.490 0.0246 -6.15 -0.599 0.0270 Tabulated from data in file AB01090.DAT & reduced using program Q06.01L Average Reynolds #: 201800 Number of angles of attack: 49 alpha / Cl / Cm -5.61 -0.582 0.0271 -4.24 -0.454 0.0293 -3.25 -0.367 0.0326 -2.24 -0.271 0.0347 -1.23 -0.189 0.0402 -0.21 -0.084 0.0437 0.74 0.049 0.0343 1.82 0.138 0.0355 2.79 0.233 0.0359 3.78 0.335 0.0358 4.77 0.440 0.0352 5.95 0.578 0.0335 6.88 0.671 0.0322 8.10 0.793 0.0303 9.02 0.887 0.0289 9.93 0.976 0.0275 11.12 1.090 0.0257 12.02 1.168 0.0241 13.22 1.230 0.0227 14.15 1.248 0.0159 14.59 0.747 -0.0841 16.04 0.763 -0.0865 17.10 0.788 -0.0905 18.20 0.799 -0.0912 18.94 0.830 -0.0957 17.28 0.776 -0.0909 16.25 0.757 -0.0886 15.25 0.737 -0.0850 14.23 0.741 -0.0857 13.22 0.735 -0.0851 12.24 0.725 -0.0824 11.27 0.729 -0.0788 10.35 0.775 -0.0693 9.72 0.957 0.0258 8.40 0.822 0.0289 7.35 0.715 0.0304 6.27 0.603 0.0321 5.37 0.493 0.0341 4.29 0.382 0.0356 3.21 0.270 0.0366 2.15 0.165 0.0369 1.06 0.069 0.0369 0.20 -0.004 0.0364 -0.85 -0.157 0.0446 -1.93 -0.236 0.0370 -3.02 -0.347 0.0352 -3.83 -0.423 0.0324 -5.01 -0.529 0.0278 -6.20 -0.648 0.0293 Tabulated from data in file AB01092.DAT & reduced using program Q06.01L Average Reynolds #: 302300 Number of angles of attack: 47 alpha / Cl / Cm -4.21 -0.487 0.0345 -3.20 -0.387 0.0369 -2.23 -0.285 0.0380 -1.27 -0.183 0.0385 -0.28 -0.107 0.0451 0.62 0.011 0.0409 1.92 0.142 0.0386 2.80 0.231 0.0386 3.81 0.354 0.0378 4.96 0.477 0.0365 5.83 0.570 0.0352 6.96 0.691 0.0333 8.03 0.805 0.0311 9.09 0.916 0.0291 9.87 0.999 0.0273 10.94 1.107 0.0249 11.99 1.203 0.0227 13.02 1.280 0.0212 14.03 1.317 0.0146 14.95 1.328 -0.0078 16.00 1.315 -0.0230 16.63 0.803 -0.0917 17.98 0.820 -0.0943 18.78 0.851 -0.0988 17.27 0.832 -0.0968 16.35 0.817 -0.0930 15.40 0.826 -0.0935 14.17 0.831 -0.0938 13.26 0.845 -0.0915 12.36 0.854 -0.0821 12.19 1.218 0.0208 10.55 1.063 0.0255 9.58 0.961 0.0283 8.37 0.838 0.0301 7.33 0.730 0.0317 6.43 0.636 0.0330 5.30 0.513 0.0349 4.40 0.419 0.0361 3.29 0.302 0.0373 2.15 0.168 0.0381 1.24 0.072 0.0381 0.27 -0.045 0.0450 -0.82 -0.157 0.0416 -2.01 -0.267 0.0391 -3.00 -0.372 0.0382 -4.01 -0.470 0.0361 -5.09 -0.572 0.0305 Tabulated from data in file AB01094.DAT & reduced using program Q06.01L Average Reynolds #: 402700 Number of angles of attack: 48 alpha / Cl / Cm -5.18 -0.608 0.0309 -3.85 -0.475 0.0363 -3.09 -0.393 0.0378 -1.88 -0.266 0.0389 -1.16 -0.187 0.0386 0.08 -0.083 0.0448 0.72 -0.022 0.0452 1.93 0.116 0.0416 2.87 0.253 0.0390 3.95 0.367 0.0379 5.00 0.477 0.0362 6.07 0.605 0.0344 7.12 0.726 0.0326 8.14 0.835 0.0303 9.14 0.942 0.0281 10.15 1.047 0.0263 11.11 1.145 0.0241 12.10 1.235 0.0220 13.48 1.310 0.0173 14.15 1.303 -0.0070 15.51 1.330 -0.0346 16.12 1.353 -0.0425 17.28 1.363 -0.0575 18.31 1.281 -0.0695 19.11 1.092 -0.0955 16.54 0.874 -0.0956 17.05 0.878 -0.0946 14.75 0.882 -0.0934 14.17 0.878 -0.0877 13.13 0.912 -0.0792 13.25 1.302 0.0200 11.26 1.154 0.0264 10.42 1.070 0.0280 9.26 0.953 0.0300 8.42 0.862 0.0314 7.18 0.724 0.0329 6.30 0.635 0.0350 4.99 0.493 0.0365 4.08 0.389 0.0377 3.14 0.282 0.0388 2.19 0.173 0.0399 0.92 0.003 0.0456 0.04 -0.083 0.0455 -0.94 -0.166 0.0400 -1.96 -0.279 0.0403 -2.99 -0.386 0.0394 -4.06 -0.485 0.0374 -5.25 -0.608 0.0308 Tabulated from data in file AB01096.DAT & reduced using program Q06.01L File ESA.LFT created on 10-24-1997 at 19:34:41 using program FORMAT :::::::::::::: FALCON.LFT :::::::::::::: Airfoil: Falcon 56 Mk III Builder: B. Devaney Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 101100 Number of angles of attack: 49 alpha / Cl / Cm -6.11 -0.478 -0.0119 -4.65 -0.414 -0.0060 -3.65 -0.348 -0.0024 -2.68 -0.206 -0.0110 -1.73 -0.072 -0.0164 -0.75 0.130 -0.0309 0.23 0.268 -0.0397 1.62 0.364 -0.0350 2.60 0.428 -0.0307 3.64 0.501 -0.0273 4.66 0.585 -0.0259 5.28 0.641 -0.0250 6.35 0.728 -0.0223 7.76 0.841 -0.0190 8.35 0.892 -0.0196 9.47 0.987 -0.0182 10.63 1.077 -0.0156 11.43 1.132 -0.0139 12.60 1.204 -0.0110 13.72 1.227 -0.0082 14.48 1.207 -0.0124 15.58 1.168 -0.0140 16.68 1.144 -0.0176 17.34 0.797 -0.0729 18.54 0.822 -0.0850 16.79 0.784 -0.0780 15.77 0.768 -0.0758 14.76 0.733 -0.0665 13.77 0.728 -0.0546 12.81 0.725 -0.0506 11.85 0.778 -0.0491 11.00 1.074 -0.0156 9.84 1.002 -0.0038 8.88 0.921 -0.0037 7.92 0.845 -0.0052 6.67 0.745 -0.0085 5.67 0.664 -0.0107 4.62 0.577 -0.0139 3.62 0.496 -0.0171 2.57 0.412 -0.0187 1.54 0.345 -0.0231 0.57 0.286 -0.0285 -0.39 0.191 -0.0275 -1.37 0.006 -0.0146 -2.33 -0.152 -0.0122 -3.59 -0.338 0.0035 -4.57 -0.406 0.0044 -5.56 -0.454 -0.0018 -6.54 -0.504 -0.0074 Tabulated from data in file CL01423.DAT & reduced using program Q06.01L Average Reynolds #: 201800 Number of angles of attack: 49 alpha / Cl / Cm -6.08 -0.509 -0.0082 -4.90 -0.415 -0.0065 -3.73 -0.243 -0.0176 -2.61 -0.132 -0.0183 -1.86 -0.071 -0.0138 -0.68 0.024 -0.0077 0.15 0.116 -0.0094 1.29 0.308 -0.0227 2.47 0.431 -0.0259 3.31 0.495 -0.0239 4.51 0.597 -0.0220 5.29 0.670 -0.0199 6.67 0.780 -0.0165 7.44 0.849 -0.0164 8.50 0.941 -0.0148 9.64 1.033 -0.0117 10.39 1.093 -0.0113 11.48 1.175 -0.0077 12.59 1.245 -0.0041 13.69 1.265 0.0013 14.69 1.223 -0.0116 15.39 1.179 -0.0156 16.54 1.137 -0.0174 17.66 1.111 -0.0231 18.72 1.115 -0.0298 16.79 1.136 -0.0228 15.84 1.161 -0.0189 14.88 1.205 -0.0167 14.02 1.263 -0.0002 12.92 1.251 0.0005 11.81 1.191 -0.0033 10.93 1.129 -0.0065 9.99 1.055 -0.0092 8.76 0.955 -0.0125 7.83 0.876 -0.0131 6.89 0.794 -0.0148 5.87 0.703 -0.0162 4.83 0.608 -0.0175 3.77 0.517 -0.0195 2.67 0.429 -0.0218 1.57 0.327 -0.0211 0.53 0.161 -0.0097 -0.44 0.039 -0.0055 -1.43 -0.043 -0.0095 -2.42 -0.123 -0.0154 -3.43 -0.221 -0.0167 -4.47 -0.368 -0.0072 -5.51 -0.479 -0.0033 -6.55 -0.536 -0.0093 Tabulated from data in file CL01425.DAT & reduced using program Q06.01L Average Reynolds #: 302400 Number of angles of attack: 51 alpha / Cl / Cm -6.22 -0.582 -0.0168 -4.83 -0.479 -0.0125 -3.95 -0.352 -0.0194 -2.64 -0.191 -0.0237 -1.67 -0.113 -0.0193 -0.78 -0.038 -0.0148 0.57 0.084 -0.0092 1.55 0.200 -0.0126 2.39 0.340 -0.0209 3.68 0.554 -0.0266 4.59 0.635 -0.0246 5.49 0.716 -0.0227 6.73 0.830 -0.0210 7.56 0.906 -0.0197 8.69 1.010 -0.0176 9.46 1.075 -0.0155 10.62 1.164 -0.0119 11.71 1.235 -0.0071 12.51 1.263 -0.0027 13.55 1.243 -0.0113 14.65 1.198 -0.0224 15.75 1.182 -0.0243 16.58 1.163 -0.0282 17.74 1.126 -0.0330 18.59 1.111 -0.0368 19.76 1.104 -0.0442 17.94 1.116 -0.0355 16.90 1.137 -0.0315 15.84 1.158 -0.0256 14.79 1.191 -0.0226 13.83 1.225 -0.0185 12.95 1.265 -0.0014 12.01 1.245 -0.0056 10.79 1.171 -0.0104 9.82 1.097 -0.0136 8.85 1.017 -0.0163 7.85 0.928 -0.0183 6.81 0.833 -0.0202 5.73 0.735 -0.0221 4.59 0.633 -0.0245 3.77 0.560 -0.0264 2.60 0.446 -0.0266 1.74 0.231 -0.0135 0.55 0.084 -0.0081 -0.49 -0.015 -0.0120 -1.60 -0.104 -0.0175 -2.44 -0.172 -0.0211 -3.71 -0.315 -0.0203 -4.48 -0.426 -0.0145 -5.76 -0.554 -0.0122 -6.59 -0.599 -0.0173 Tabulated from data in file CL01446.DAT & reduced using program Q06.01L Average Reynolds #: 403200 Number of angles of attack: 47 alpha / Cl / Cm -4.86 -0.454 -0.0177 -3.59 -0.299 -0.0221 -2.63 -0.199 -0.0210 -1.67 -0.115 -0.0175 -0.75 -0.032 -0.0137 0.28 0.066 -0.0100 1.31 0.167 -0.0087 2.40 0.405 -0.0184 3.26 0.528 -0.0247 4.60 0.662 -0.0238 5.54 0.750 -0.0222 6.41 0.832 -0.0205 7.61 0.945 -0.0182 8.40 1.017 -0.0165 9.92 1.139 -0.0108 10.37 1.173 -0.0097 11.51 1.240 -0.0045 12.56 1.243 -0.0059 13.92 1.182 -0.0184 14.34 1.161 -0.0191 15.51 1.167 -0.0247 16.69 1.118 -0.0311 17.56 1.100 -0.0349 18.79 1.093 -0.0401 16.96 1.108 -0.0335 15.91 1.131 -0.0304 14.91 1.196 -0.0247 13.92 1.179 -0.0201 12.79 1.238 -0.0099 11.97 1.253 -0.0011 10.87 1.207 -0.0065 9.95 1.139 -0.0096 8.78 1.047 -0.0132 7.81 0.963 -0.0159 6.80 0.869 -0.0180 5.73 0.767 -0.0191 4.64 0.665 -0.0208 3.82 0.591 -0.0230 2.73 0.457 -0.0198 1.72 0.303 -0.0116 0.30 0.066 -0.0085 -0.50 -0.014 -0.0117 -1.76 -0.126 -0.0170 -2.68 -0.207 -0.0207 -4.14 -0.370 -0.0205 -4.35 -0.396 -0.0198 -5.74 -0.558 -0.0142 Tabulated from data in file CL01449.DAT & reduced using program Q06.01L File FALCON.LFT created on 10-24-1997 at 19:34:41 using program FORMAT :::::::::::::: GOE417A.LFT :::::::::::::: Airfoil: Goe 417a Builder: M. Fox Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 60200 Number of angles of attack: 49 alpha / Cl / Cm -5.14 -0.329 0.0177 -3.59 -0.325 0.0043 -3.08 -0.306 0.0004 -1.60 -0.186 -0.0225 -0.59 -0.068 -0.0359 0.41 0.083 -0.0549 1.45 0.264 -0.0730 2.49 0.442 -0.0892 3.55 0.601 -0.1022 4.62 0.794 -0.1148 5.63 0.939 -0.1129 6.64 1.043 -0.1039 7.64 1.125 -0.0943 8.61 1.193 -0.0848 9.57 1.265 -0.0805 10.63 1.315 -0.0722 11.57 1.344 -0.0631 12.52 1.363 -0.0559 13.60 1.396 -0.0620 14.56 1.300 -0.1251 15.54 1.236 -0.1355 16.55 1.234 -0.1450 17.57 1.235 -0.1660 18.55 1.251 -0.1689 19.52 1.268 -0.1767 17.55 1.242 -0.1742 16.62 1.199 -0.1656 15.62 1.227 -0.1486 14.70 1.308 -0.1226 13.79 1.380 -0.1011 12.88 1.382 -0.0688 11.54 1.345 -0.0682 10.70 1.324 -0.0738 9.83 1.284 -0.0817 8.48 1.203 -0.0940 7.49 1.113 -0.1012 6.59 1.030 -0.1071 5.56 0.945 -0.1212 4.62 0.805 -0.1238 3.68 0.637 -0.1129 2.34 0.436 -0.0979 1.46 0.277 -0.0867 0.53 0.117 -0.0715 -0.81 -0.083 -0.0439 -1.70 -0.179 -0.0322 -2.58 -0.241 -0.0176 -3.90 -0.303 0.0064 -4.78 -0.312 0.0114 -5.71 -0.312 0.0150 Tabulated from data in file PG01724.DAT & reduced using program Q06.01L Average Reynolds #: 100000 Number of angles of attack: 49 alpha / Cl / Cm -5.20 -0.320 0.0236 -3.70 -0.313 0.0170 -2.57 -0.232 -0.0023 -1.81 -0.136 -0.0233 -0.65 0.063 -0.0605 0.15 0.226 -0.0826 1.35 0.434 -0.1047 2.16 0.565 -0.1142 3.43 0.749 -0.1200 4.30 0.847 -0.1158 5.59 0.965 -0.1041 6.44 1.043 -0.0989 7.29 1.106 -0.0925 8.48 1.187 -0.0842 9.67 1.254 -0.0757 10.46 1.286 -0.0677 11.60 1.327 -0.0593 12.39 1.354 -0.0533 13.50 1.355 -0.0529 14.53 1.284 -0.1301 15.28 1.169 -0.1447 16.43 1.182 -0.1625 17.66 1.187 -0.1657 18.48 1.190 -0.1690 19.71 1.196 -0.1682 17.86 1.152 -0.1676 16.73 1.197 -0.1673 15.60 1.187 -0.1596 14.90 1.223 -0.1479 13.90 1.330 -0.0955 12.93 1.356 -0.0573 11.92 1.337 -0.0594 10.89 1.296 -0.0652 9.87 1.255 -0.0732 8.84 1.201 -0.0807 7.77 1.132 -0.0877 6.67 1.051 -0.0962 5.56 0.953 -0.1041 4.81 0.886 -0.1120 3.66 0.755 -0.1190 2.52 0.594 -0.1148 1.42 0.420 -0.1041 0.70 0.300 -0.0933 -0.41 0.095 -0.0681 -1.50 -0.105 -0.0352 -2.54 -0.228 -0.0082 -3.55 -0.303 0.0103 -4.55 -0.311 0.0189 -5.57 -0.297 0.0169 Tabulated from data in file PG01125.DAT & reduced using program Q06.01L Average Reynolds #: 199700 Number of angles of attack: 49 alpha / Cl / Cm -5.15 -0.363 0.0239 -3.84 -0.299 0.0038 -2.85 -0.147 -0.0317 -1.90 0.040 -0.0681 -0.93 0.231 -0.0981 0.32 0.466 -0.1191 1.37 0.615 -0.1204 2.48 0.745 -0.1158 3.29 0.832 -0.1126 4.47 0.944 -0.1073 5.32 1.019 -0.1027 6.57 1.120 -0.0967 7.40 1.177 -0.0906 8.60 1.245 -0.0823 9.77 1.302 -0.0728 10.57 1.336 -0.0662 11.67 1.369 -0.0588 12.43 1.371 -0.0536 13.19 1.350 -0.0963 14.46 1.255 -0.1579 15.36 1.235 -0.1674 16.45 1.206 -0.1712 17.35 1.182 -0.1703 18.53 1.171 -0.1727 19.37 1.170 -0.1745 17.58 1.172 -0.1734 16.45 1.210 -0.1735 15.73 1.233 -0.1747 14.75 1.262 -0.1618 13.88 1.314 -0.1323 12.99 1.369 -0.0552 11.73 1.365 -0.0543 10.78 1.339 -0.0606 9.79 1.302 -0.0690 8.76 1.251 -0.0757 7.69 1.194 -0.0844 6.55 1.124 -0.0932 5.80 1.069 -0.0978 4.62 0.967 -0.1030 3.80 0.891 -0.1068 2.53 0.754 -0.1134 1.34 0.615 -0.1186 0.58 0.519 -0.1215 -0.34 0.347 -0.1129 -1.34 0.153 -0.0883 -2.63 -0.111 -0.0416 -3.50 -0.260 -0.0079 -4.72 -0.364 0.0204 -5.63 -0.369 0.0248 Tabulated from data in file CL01127.DAT & reduced using program Q06.01L Average Reynolds #: 299700 Number of angles of attack: 49 alpha / Cl / Cm -5.70 -0.398 0.0110 -4.83 -0.311 -0.0030 -2.69 0.024 -0.0728 -1.81 0.159 -0.0937 -0.77 0.360 -0.1130 0.32 0.508 -0.1181 1.19 0.618 -0.1187 2.39 0.759 -0.1162 3.34 0.859 -0.1129 4.32 0.956 -0.1086 5.33 1.049 -0.1046 6.42 1.132 -0.0982 7.56 1.209 -0.0914 8.41 1.258 -0.0853 9.61 1.324 -0.0762 10.50 1.363 -0.0690 11.73 1.397 -0.0594 12.53 1.397 -0.0549 13.22 1.390 -0.0834 14.30 1.367 -0.1362 15.22 1.312 -0.1645 16.41 1.284 -0.1749 17.06 1.288 -0.1827 17.55 1.249 -0.1791 19.30 1.193 -0.1759 17.41 1.272 -0.1816 16.61 1.295 -0.1739 15.71 1.300 -0.1727 14.64 1.333 -0.1530 14.02 1.369 -0.1270 13.40 1.382 -0.0984 11.70 1.392 -0.0575 10.72 1.365 -0.0631 9.66 1.321 -0.0712 8.51 1.259 -0.0805 7.65 1.210 -0.0862 6.76 1.151 -0.0920 5.50 1.059 -0.0997 4.68 0.985 -0.1035 3.47 0.868 -0.1091 2.68 0.784 -0.1124 1.62 0.665 -0.1162 0.59 0.541 -0.1174 -0.36 0.415 -0.1150 -1.42 0.252 -0.1048 -2.67 0.028 -0.0746 -3.69 -0.119 -0.0459 -4.47 -0.261 -0.0167 -5.55 -0.380 0.0084 Tabulated from data in file CL01129.DAT & reduced using program Q06.01L Average Reynolds #: 398900 Number of angles of attack: 13 alpha / Cl / Cm -2.34 0.185 -0.0950 -0.86 0.424 -0.1120 0.25 0.581 -0.1153 1.39 0.721 -0.1135 2.27 0.823 -0.1104 3.57 0.955 -0.1050 4.28 1.020 -0.1022 5.51 1.117 -0.0959 6.46 1.188 -0.0912 7.87 1.274 -0.0820 8.92 1.332 -0.0750 9.50 1.360 -0.0707 10.71 1.407 -0.0622 Tabulated from data in file CL01131.DAT & reduced using program Q06.01L File GOE417A.LFT created on 10-24-1997 at 19:34:41 using program FORMAT :::::::::::::: LRN1007B.LFT :::::::::::::: Airfoil: LRN1007 (B) Builder: M. Allen Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60000 Number of angles of attack: 49 alpha / Cl / Cm -6.45 -0.329 0.0223 -5.01 -0.343 0.0110 -4.08 -0.321 -0.0060 -3.13 -0.244 -0.0317 -2.14 -0.096 -0.0604 -1.19 0.092 -0.0922 0.26 0.295 -0.1074 0.83 0.348 -0.1054 2.28 0.478 -0.1042 3.26 0.548 -0.1062 4.26 0.619 -0.1091 5.24 0.679 -0.1097 6.22 0.734 -0.1111 7.19 0.797 -0.1141 8.15 0.893 -0.1171 9.19 1.271 -0.1039 10.11 1.258 -0.0890 11.49 1.248 -0.0737 12.41 1.254 -0.0670 13.33 1.260 -0.0600 14.27 1.263 -0.0587 15.16 1.269 -0.0580 16.23 1.326 -0.0864 17.18 1.339 -0.1170 18.12 1.293 -0.1480 16.40 1.351 -0.1011 15.49 1.269 -0.0740 14.56 1.265 -0.0596 13.28 1.252 -0.0643 12.49 1.250 -0.0698 11.64 1.245 -0.0771 10.39 1.252 -0.0919 9.57 1.259 -0.1031 8.22 0.982 -0.1164 7.27 0.816 -0.1142 6.41 0.757 -0.1140 5.06 0.667 -0.1088 4.22 0.627 -0.1120 3.33 0.570 -0.1103 2.43 0.508 -0.1142 1.14 0.389 -0.1129 0.28 0.315 -0.1115 -1.01 0.149 -0.1015 -1.86 0.009 -0.0871 -2.72 -0.144 -0.0568 -3.95 -0.306 -0.0120 -4.83 -0.333 0.0074 -6.11 -0.314 0.0107 -6.95 -0.287 0.0074 Tabulated from data in file AB01696.DAT & reduced using program Q06.01L Average Reynolds #: 100400 Number of angles of attack: 49 alpha / Cl / Cm -6.42 -0.365 0.0165 -5.11 -0.375 0.0113 -4.17 -0.307 -0.0135 -3.20 -0.110 -0.0562 -2.16 0.121 -0.0928 -1.18 0.258 -0.1065 -0.12 0.349 -0.1104 1.20 0.458 -0.1085 1.89 0.510 -0.1092 2.96 0.592 -0.1102 4.00 0.671 -0.1100 5.03 0.781 -0.1102 6.09 0.965 -0.1138 7.19 1.250 -0.1098 8.16 1.273 -0.0973 9.42 1.252 -0.0827 10.08 1.264 -0.0812 11.08 1.267 -0.0724 12.04 1.277 -0.0702 13.31 1.283 -0.0659 14.27 1.291 -0.0666 15.30 1.364 -0.0967 16.29 1.382 -0.1172 17.31 1.362 -0.1476 18.32 1.293 -0.1648 16.53 1.390 -0.1515 15.59 1.365 -0.1232 14.42 1.277 -0.0667 13.51 1.282 -0.0657 12.60 1.274 -0.0641 11.50 1.261 -0.0690 10.63 1.252 -0.0732 9.54 1.248 -0.0828 8.68 1.253 -0.0911 7.58 1.256 -0.1062 6.38 1.041 -0.1201 5.42 0.817 -0.1117 4.47 0.710 -0.1125 3.26 0.610 -0.1105 2.31 0.538 -0.1084 1.39 0.462 -0.1082 0.22 0.364 -0.1072 -0.68 0.288 -0.1090 -1.82 0.161 -0.1058 -2.77 -0.038 -0.0783 -3.80 -0.259 -0.0376 -4.95 -0.381 -0.0026 -5.84 -0.389 0.0077 -6.95 -0.346 0.0032 Tabulated from data in file AB01364.DAT & reduced using program Q06.01L Average Reynolds #: 200200 Number of angles of attack: 49 alpha / Cl / Cm -6.38 -0.183 -0.0314 -4.87 -0.116 -0.0579 -3.88 -0.056 -0.0797 -2.91 0.066 -0.1090 -1.90 0.205 -0.1299 -0.96 0.328 -0.1369 0.06 0.444 -0.1374 0.33 0.558 -0.1358 2.21 0.783 -0.1339 3.19 0.896 -0.1317 4.39 1.028 -0.1280 5.54 1.153 -0.1241 6.12 1.215 -0.1202 7.22 1.229 -0.1054 8.24 1.236 -0.0938 9.23 1.245 -0.0839 10.26 1.261 -0.0767 11.19 1.275 -0.0710 12.11 1.291 -0.0663 13.51 1.362 -0.0646 14.43 1.383 -0.0952 15.36 1.414 -0.1223 16.19 1.411 -0.1475 17.14 1.370 -0.1686 18.10 1.285 -0.1840 16.14 1.429 -0.1453 15.59 1.411 -0.1261 14.24 1.371 -0.0874 13.32 1.347 -0.0681 12.38 1.303 -0.0700 11.43 1.284 -0.0748 10.48 1.267 -0.0800 9.57 1.256 -0.0865 8.18 1.241 -0.0987 7.22 1.235 -0.1105 6.61 1.232 -0.1186 5.03 1.099 -0.1312 4.39 1.029 -0.1331 3.11 0.881 -0.1360 2.47 0.808 -0.1374 1.39 0.683 -0.1381 0.22 0.523 -0.1406 -0.79 0.359 -0.1420 -1.75 0.230 -0.1366 -3.28 0.016 -0.1032 -3.82 -0.046 -0.0861 -5.19 -0.127 -0.0566 -5.77 -0.154 -0.0453 -7.12 -0.198 -0.0282 Tabulated from data in file AB01699.DAT & reduced using program Q06.01L Average Reynolds #: 300400 Number of angles of attack: 49 alpha / Cl / Cm -6.35 -0.184 -0.0355 -5.14 -0.094 -0.0652 -4.27 0.019 -0.0940 -3.28 0.178 -0.1256 -2.16 0.351 -0.1412 -1.17 0.473 -0.1432 0.04 0.612 -0.1418 0.87 0.705 -0.1410 1.86 0.814 -0.1351 3.07 0.940 -0.1348 4.14 1.051 -0.1340 5.01 1.139 -0.1332 6.11 1.224 -0.1273 7.32 1.234 -0.1092 8.25 1.246 -0.1006 9.50 1.267 -0.0919 10.22 1.281 -0.0856 11.25 1.303 -0.0789 12.28 1.355 -0.0747 13.31 1.444 -0.0745 14.16 1.441 -0.0965 14.93 1.463 -0.1191 16.09 1.452 -0.1433 17.18 1.412 -0.1737 18.08 1.328 -0.1846 16.44 1.446 -0.1568 15.66 1.481 -0.1388 14.81 1.440 -0.1161 13.49 1.443 -0.0755 12.65 1.385 -0.0716 11.44 1.308 -0.0752 10.54 1.286 -0.0790 9.58 1.266 -0.0847 8.59 1.250 -0.0918 7.52 1.237 -0.1020 6.47 1.228 -0.1153 5.41 1.178 -0.1249 4.42 1.076 -0.1268 3.46 0.975 -0.1283 2.55 0.879 -0.1304 1.32 0.753 -0.1339 0.43 0.658 -0.1358 -0.75 0.524 -0.1385 -1.81 0.395 -0.1392 -2.78 0.262 -0.1351 -3.72 0.102 -0.1141 -4.74 -0.046 -0.0798 -5.79 -0.156 -0.0444 -6.72 -0.210 -0.0251 Tabulated from data in file AB01362.DAT & reduced using program Q06.01L File LRN1007B.LFT created on 10-24-1997 at 19:34:41 using program FORMAT :::::::::::::: PT40A.LFT :::::::::::::: Airfoil: PT-40 (A) Builder: T. Lampe Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 100800 Number of angles of attack: 49 alpha / Cl / Cm -6.37 -0.354 0.0131 -5.20 -0.357 0.0028 -4.31 -0.332 -0.0113 -3.10 -0.179 -0.0415 -2.15 -0.052 -0.0548 -0.59 0.190 -0.0747 0.05 0.287 -0.0795 1.02 0.394 -0.0811 2.03 0.486 -0.0744 3.02 0.581 -0.0688 4.02 0.666 -0.0631 5.00 0.744 -0.0580 6.26 0.852 -0.0533 7.23 0.936 -0.0506 8.19 1.012 -0.0472 9.10 1.071 -0.0424 10.27 1.141 -0.0366 11.17 1.185 -0.0325 12.51 1.224 -0.0266 13.03 1.016 -0.0982 14.18 0.803 -0.1158 15.14 0.817 -0.1191 16.12 0.860 -0.1243 17.07 0.848 -0.1229 18.60 0.932 -0.1347 16.63 0.837 -0.1284 15.48 0.826 -0.1287 14.64 0.823 -0.1267 13.52 0.811 -0.1205 12.32 0.861 -0.1141 11.54 1.199 -0.0350 10.79 1.164 -0.0333 9.37 1.089 -0.0397 8.63 1.044 -0.0433 7.58 0.969 -0.0478 6.50 0.881 -0.0509 5.28 0.772 -0.0540 4.48 0.712 -0.0579 3.62 0.642 -0.0624 2.45 0.538 -0.0692 1.19 0.420 -0.0789 0.36 0.334 -0.0804 -0.50 0.214 -0.0763 -1.62 0.040 -0.0604 -2.72 -0.119 -0.0466 -3.91 -0.287 -0.0175 -4.66 -0.343 -0.0022 -5.69 -0.351 0.0090 -6.73 -0.345 0.0175 Tabulated from data in file CL01020.DAT & reduced using program Q06.01L Average Reynolds #: 201300 Number of angles of attack: 49 alpha / Cl / Cm -6.65 -0.375 0.0236 -5.13 -0.340 -0.0033 -3.87 -0.134 -0.0602 -2.93 0.001 -0.0757 -2.02 0.098 -0.0779 -1.11 0.186 -0.0743 0.12 0.305 -0.0714 1.05 0.397 -0.0683 2.00 0.493 -0.0661 3.44 0.632 -0.0611 4.06 0.686 -0.0587 5.01 0.770 -0.0553 6.23 0.874 -0.0514 7.14 0.948 -0.0480 8.05 1.018 -0.0436 9.19 1.096 -0.0378 10.47 1.165 -0.0300 11.38 1.207 -0.0251 12.20 1.236 -0.0209 13.26 1.258 -0.0178 14.37 1.267 -0.0186 14.80 0.834 -0.1251 16.12 0.849 -0.1266 17.27 0.861 -0.1269 18.12 0.880 -0.1284 16.52 0.847 -0.1280 15.28 0.821 -0.1245 14.34 0.829 -0.1265 13.52 0.855 -0.1272 12.45 0.936 -0.1137 11.95 1.235 -0.0244 10.61 1.178 -0.0306 9.72 1.133 -0.0356 8.49 1.054 -0.0420 7.49 0.982 -0.0469 6.73 0.920 -0.0499 5.67 0.826 -0.0535 4.60 0.729 -0.0573 3.47 0.628 -0.0617 2.60 0.550 -0.0646 1.49 0.444 -0.0675 0.25 0.322 -0.0706 -0.61 0.236 -0.0722 -1.50 0.151 -0.0746 -2.68 0.034 -0.0767 -3.56 -0.085 -0.0675 -4.64 -0.258 -0.0284 -5.62 -0.373 0.0115 -6.75 -0.375 0.0225 Tabulated from data in file CL01022.DAT & reduced using program Q06.01L Average Reynolds #: 302100 Number of angles of attack: 49 alpha / Cl / Cm -6.19 -0.382 0.0135 -4.87 -0.233 -0.0372 -4.28 -0.145 -0.0589 -3.09 -0.002 -0.0748 -2.05 0.097 -0.0732 -0.96 0.204 -0.0704 -0.11 0.292 -0.0684 1.03 0.408 -0.0661 1.95 0.500 -0.0642 3.20 0.618 -0.0608 4.20 0.710 -0.0583 5.22 0.803 -0.0556 6.31 0.904 -0.0526 7.61 1.014 -0.0477 8.29 1.067 -0.0447 9.27 1.136 -0.0395 10.22 1.196 -0.0340 11.15 1.245 -0.0286 12.30 1.293 -0.0219 13.16 1.314 -0.0181 14.27 1.334 -0.0166 15.47 1.342 -0.0226 15.62 0.875 -0.1285 16.96 0.888 -0.1306 18.03 0.928 -0.1346 16.56 0.885 -0.1317 15.51 0.873 -0.1294 14.44 0.890 -0.1285 13.40 0.977 -0.1202 13.21 1.317 -0.0189 11.77 1.274 -0.0241 10.62 1.215 -0.0300 9.64 1.158 -0.0351 8.58 1.085 -0.0407 7.39 0.992 -0.0462 6.53 0.919 -0.0494 5.60 0.837 -0.0525 4.12 0.702 -0.0569 3.44 0.637 -0.0589 2.31 0.531 -0.0626 1.28 0.431 -0.0655 0.29 0.329 -0.0677 -0.69 0.231 -0.0699 -1.61 0.139 -0.0722 -2.92 0.014 -0.0753 -3.83 -0.084 -0.0689 -4.64 -0.197 -0.0467 -5.68 -0.338 -0.0025 -6.72 -0.386 0.0213 Tabulated from data in file CL01024.DAT & reduced using program Q06.01L Average Reynolds #: 402500 Number of angles of attack: 49 alpha / Cl / Cm -6.40 -0.392 0.0079 -5.21 -0.257 -0.0349 -4.32 -0.147 -0.0606 -3.26 -0.025 -0.0719 -2.27 0.071 -0.0716 -1.05 0.197 -0.0690 -0.15 0.291 -0.0673 0.92 0.402 -0.0655 2.06 0.516 -0.0633 3.08 0.611 -0.0605 4.21 0.718 -0.0581 5.09 0.800 -0.0559 6.05 0.887 -0.0532 7.35 0.996 -0.0481 8.67 1.101 -0.0427 9.51 1.159 -0.0381 10.18 1.202 -0.0340 11.58 1.271 -0.0254 12.19 1.294 -0.0219 13.30 1.323 -0.0179 14.42 1.343 -0.0200 15.25 1.349 -0.0240 16.33 1.342 -0.0353 16.49 0.950 -0.1312 17.99 0.993 -0.1359 16.53 0.971 -0.1342 15.44 0.957 -0.1309 14.56 1.003 -0.1269 13.68 1.080 -0.1165 13.57 1.340 -0.0187 11.63 1.288 -0.0229 10.64 1.239 -0.0285 9.59 1.176 -0.0346 8.35 1.088 -0.0413 7.31 1.003 -0.0453 6.61 0.952 -0.0480 5.44 0.843 -0.0516 4.52 0.749 -0.0541 3.23 0.633 -0.0575 2.39 0.553 -0.0601 1.22 0.434 -0.0635 0.47 0.358 -0.0648 -0.57 0.246 -0.0673 -1.55 0.147 -0.0694 -2.79 0.023 -0.0717 -3.57 -0.061 -0.0702 -4.85 -0.215 -0.0478 -5.66 -0.318 -0.0192 -6.80 -0.426 0.0159 Tabulated from data in file AB01026.DAT & reduced using program Q06.01L File PT40A.LFT created on 10-24-1997 at 19:34:41 using program FORMAT :::::::::::::: PT40B.LFT :::::::::::::: Airfoil: PT-40 (B) Builder: T. Lampe Comment: clean; open bay Number of Reynolds #'s: 4 Average Reynolds #: 100900 Number of angles of attack: 49 alpha / Cl / Cm -5.77 -0.355 0.0201 -4.24 -0.328 -0.0075 -3.43 -0.185 -0.0407 -2.25 -0.012 -0.0631 -1.43 0.103 -0.0723 -0.21 0.240 -0.0737 0.60 0.323 -0.0715 1.96 0.439 -0.0679 2.83 0.511 -0.0665 3.68 0.587 -0.0629 4.98 0.689 -0.0573 5.82 0.753 -0.0547 7.09 0.858 -0.0505 7.92 0.937 -0.0482 8.73 0.998 -0.0437 9.94 1.080 -0.0380 10.73 1.124 -0.0334 11.92 1.187 -0.0296 13.13 1.232 -0.0257 14.00 0.787 -0.1162 14.83 0.816 -0.1219 16.05 0.833 -0.1266 16.90 0.834 -0.1254 17.75 0.838 -0.1261 19.00 0.879 -0.1322 17.09 0.807 -0.1290 15.94 0.824 -0.1312 15.13 0.804 -0.1302 14.01 0.799 -0.1234 13.22 0.795 -0.1217 12.22 0.864 -0.1114 11.30 1.162 -0.0389 10.28 1.101 -0.0389 9.24 1.033 -0.0434 8.18 0.967 -0.0491 7.09 0.867 -0.0512 5.97 0.772 -0.0553 5.20 0.705 -0.0572 4.06 0.619 -0.0616 2.92 0.521 -0.0671 2.13 0.447 -0.0697 0.97 0.352 -0.0749 -0.26 0.242 -0.0785 -1.05 0.154 -0.0792 -2.13 0.007 -0.0707 -3.22 -0.155 -0.0502 -4.31 -0.333 -0.0110 -5.34 -0.344 0.0068 -6.10 -0.362 0.0136 Tabulated from data in file CL01065.DAT & reduced using program Q06.01L Average Reynolds #: 201200 Number of angles of attack: 53 alpha / Cl / Cm -5.74 -0.324 -0.0049 -4.33 -0.170 -0.0546 -3.58 -0.090 -0.0665 -2.40 0.034 -0.0728 -1.00 0.157 -0.0723 -0.18 0.238 -0.0706 0.72 0.333 -0.0692 2.00 0.459 -0.0661 2.82 0.539 -0.0636 4.00 0.647 -0.0596 4.88 0.724 -0.0567 5.75 0.800 -0.0538 7.06 0.914 -0.0497 7.90 0.987 -0.0470 9.12 1.083 -0.0418 9.93 1.140 -0.0380 11.12 1.212 -0.0315 11.88 1.240 -0.0274 13.05 1.272 -0.0222 13.81 1.287 -0.0211 15.32 1.263 -0.0270 14.98 0.831 -0.1307 16.85 0.851 -0.1302 17.94 0.873 -0.1323 19.01 0.905 -0.1371 19.73 0.930 -0.1402 21.07 0.956 -0.1448 18.87 0.907 -0.1399 18.09 0.875 -0.1358 16.51 0.860 -0.1354 16.34 0.850 -0.1349 15.17 0.850 -0.1332 14.05 0.835 -0.1283 12.97 0.868 -0.1218 12.51 1.254 -0.0256 11.17 1.211 -0.0329 10.10 1.145 -0.0373 9.03 1.073 -0.0423 8.27 1.016 -0.0459 7.13 0.921 -0.0499 5.96 0.817 -0.0534 5.11 0.743 -0.0558 3.89 0.640 -0.0601 3.01 0.565 -0.0635 1.92 0.453 -0.0672 1.05 0.363 -0.0683 -0.14 0.244 -0.0707 -0.99 0.159 -0.0722 -2.40 0.034 -0.0725 -3.23 -0.049 -0.0704 -4.35 -0.167 -0.0563 -5.10 -0.255 -0.0331 -6.05 -0.345 0.0071 Tabulated from data in file CL01067.DAT & reduced using program Q06.01L Average Reynolds #: 302000 Number of angles of attack: 53 alpha / Cl / Cm -5.83 -0.319 -0.0135 -4.64 -0.195 -0.0509 -3.47 -0.063 -0.0705 -2.34 0.038 -0.0723 -1.24 0.143 -0.0708 -0.35 0.252 -0.0692 0.80 0.367 -0.0671 1.62 0.449 -0.0655 2.83 0.560 -0.0625 3.68 0.635 -0.0602 4.92 0.745 -0.0573 5.76 0.821 -0.0555 7.10 0.930 -0.0508 8.00 1.008 -0.0478 8.89 1.077 -0.0440 10.16 1.166 -0.0379 11.01 1.218 -0.0335 12.22 1.272 -0.0266 12.99 1.298 -0.0233 14.10 1.323 -0.0232 14.82 1.335 -0.0252 15.43 1.243 -0.0669 16.67 0.940 -0.1345 17.95 0.930 -0.1376 18.68 0.948 -0.1409 19.68 0.970 -0.1424 20.88 0.989 -0.1475 19.09 0.974 -0.1428 18.17 0.937 -0.1374 16.58 0.956 -0.1354 16.17 0.928 -0.1357 15.20 0.926 -0.1352 13.97 0.927 -0.1305 13.20 1.028 -0.1137 13.43 1.310 -0.0232 11.16 1.230 -0.0315 10.11 1.169 -0.0366 9.03 1.093 -0.0417 8.23 1.031 -0.0453 7.05 0.933 -0.0493 5.82 0.833 -0.0538 4.92 0.750 -0.0559 4.03 0.668 -0.0581 2.71 0.546 -0.0621 1.85 0.465 -0.0644 0.99 0.382 -0.0667 -0.21 0.264 -0.0695 -1.22 0.145 -0.0713 -1.98 0.069 -0.0722 -3.30 -0.043 -0.0720 -4.01 -0.118 -0.0659 -5.17 -0.255 -0.0360 -6.34 -0.368 -0.0004 Tabulated from data in file CL01069.DAT & reduced using program Q06.01L Average Reynolds #: 402100 Number of angles of attack: 22 alpha / Cl / Cm -5.86 -0.316 -0.0230 -4.70 -0.184 -0.0570 -3.47 -0.048 -0.0710 -2.34 0.050 -0.0710 -1.58 0.142 -0.0698 -0.48 0.255 -0.0681 0.74 0.379 -0.0661 1.69 0.471 -0.0642 2.73 0.568 -0.0619 3.83 0.672 -0.0600 5.00 0.785 -0.0576 5.88 0.863 -0.0554 7.16 0.970 -0.0519 8.09 1.047 -0.0482 9.05 1.116 -0.0438 10.00 1.180 -0.0389 10.93 1.235 -0.0340 12.23 1.298 -0.0272 13.02 1.326 -0.0241 14.15 1.365 -0.0214 15.15 1.384 -0.0239 15.99 1.398 -0.0338 Tabulated from data in file CL01071.DAT & reduced using program Q06.01L File PT40B.LFT created on 10-24-1997 at 19:34:41 using program FORMAT :::::::::::::: RG14.LFT :::::::::::::: Airfoil: RG14 Builder: R. Cavazos Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60400 Number of angles of attack: 49 alpha / Cl / Cm -6.16 -0.494 -0.0373 -4.64 -0.375 -0.0365 -3.86 -0.312 -0.0327 -2.71 -0.221 -0.0251 -1.94 -0.150 -0.0142 -0.82 -0.065 -0.0193 0.37 0.053 -0.0228 1.13 0.125 -0.0150 2.34 0.342 -0.0355 3.54 0.509 -0.0383 4.34 0.572 -0.0329 5.53 0.679 -0.0349 6.31 0.737 -0.0346 7.48 0.821 -0.0315 8.63 0.904 -0.0283 9.37 0.939 -0.0242 10.49 0.986 -0.0233 11.59 0.937 -0.0717 12.31 0.887 -0.1036 13.46 0.841 -0.1124 14.59 0.841 -0.1183 15.35 0.832 -0.1198 16.54 0.893 -0.1321 17.70 0.901 -0.1369 18.47 0.913 -0.1411 16.79 0.880 -0.1355 15.75 0.887 -0.1402 14.69 0.855 -0.1317 13.67 0.845 -0.1232 12.68 0.836 -0.1194 11.68 0.908 -0.1070 10.73 0.984 -0.0434 9.76 0.964 -0.0287 8.79 0.921 -0.0298 7.80 0.865 -0.0332 6.78 0.797 -0.0364 5.74 0.723 -0.0408 4.69 0.622 -0.0478 3.63 0.530 -0.0531 2.56 0.403 -0.0552 1.51 0.192 -0.0321 0.49 0.101 -0.0265 -0.51 -0.006 -0.0197 -1.50 -0.108 -0.0256 -2.49 -0.188 -0.0287 -3.50 -0.267 -0.0292 -4.48 -0.347 -0.0316 -5.53 -0.436 -0.0350 -6.57 -0.509 -0.0321 Tabulated from data in file AB01057.DAT & reduced using program Q06.01L Average Reynolds #: 100700 Number of angles of attack: 49 alpha / Cl / Cm -6.09 -0.431 -0.0369 -4.95 -0.336 -0.0345 -3.78 -0.245 -0.0311 -2.61 -0.145 -0.0294 -1.85 -0.096 -0.0196 -0.66 -0.005 -0.0218 0.10 0.061 -0.0215 1.31 0.218 -0.0395 2.53 0.407 -0.0489 3.34 0.498 -0.0483 4.58 0.613 -0.0426 5.39 0.682 -0.0399 6.62 0.801 -0.0382 7.39 0.862 -0.0355 8.56 0.945 -0.0313 9.34 0.993 -0.0284 10.46 1.040 -0.0239 11.55 1.005 -0.0738 12.65 0.922 -0.1150 13.41 0.905 -0.1228 14.61 0.946 -0.1355 15.38 0.920 -0.1320 16.59 0.920 -0.1337 17.40 0.937 -0.1384 18.61 0.949 -0.1373 16.82 0.913 -0.1395 15.72 0.928 -0.1414 14.63 0.927 -0.1384 13.88 0.929 -0.1364 12.83 0.928 -0.1290 11.82 0.988 -0.1037 10.84 1.042 -0.0290 9.88 1.020 -0.0274 8.88 0.965 -0.0302 7.86 0.904 -0.0339 6.81 0.823 -0.0368 5.76 0.725 -0.0385 4.69 0.625 -0.0417 3.62 0.524 -0.0480 2.52 0.410 -0.0529 1.45 0.256 -0.0462 0.71 0.137 -0.0318 -0.32 0.036 -0.0229 -1.36 -0.060 -0.0176 -2.38 -0.130 -0.0236 -3.40 -0.209 -0.0263 -4.42 -0.295 -0.0282 -5.47 -0.376 -0.0312 -6.54 -0.474 -0.0297 Tabulated from data in file AB01059.DAT & reduced using program Q06.01L Average Reynolds #: 201100 Number of angles of attack: 49 alpha / Cl / Cm -6.41 -0.492 -0.0309 -4.39 -0.322 -0.0309 -3.93 -0.282 -0.0302 -2.66 -0.170 -0.0298 -1.85 -0.097 -0.0298 -0.59 0.069 -0.0374 0.25 0.195 -0.0455 1.51 0.351 -0.0486 2.35 0.431 -0.0466 3.63 0.550 -0.0432 4.44 0.624 -0.0415 5.27 0.700 -0.0399 6.53 0.812 -0.0370 7.34 0.881 -0.0346 8.54 0.974 -0.0308 9.72 1.054 -0.0268 10.47 1.084 -0.0227 11.56 1.089 -0.0448 12.55 1.077 -0.1022 13.60 1.027 -0.1251 14.30 1.009 -0.1321 15.36 0.945 -0.1355 16.44 0.937 -0.1357 17.52 0.943 -0.1376 18.60 0.960 -0.1410 16.78 0.943 -0.1393 15.66 0.941 -0.1356 14.90 0.996 -0.1375 13.81 1.032 -0.1311 12.74 1.064 -0.1117 11.75 1.088 -0.0694 11.12 1.095 -0.0215 9.86 1.061 -0.0255 8.86 0.997 -0.0291 7.83 0.918 -0.0319 6.77 0.831 -0.0350 5.68 0.739 -0.0382 4.56 0.637 -0.0410 3.79 0.566 -0.0428 2.70 0.464 -0.0452 1.55 0.350 -0.0476 0.75 0.259 -0.0472 -0.72 0.049 -0.0360 -1.82 -0.091 -0.0285 -2.52 -0.157 -0.0272 -3.62 -0.257 -0.0265 -4.39 -0.323 -0.0277 -5.54 -0.410 -0.0316 -6.72 -0.517 -0.0261 Tabulated from data in file AB01061.DAT & reduced using program Q06.01L Average Reynolds #: 301900 Number of angles of attack: 49 alpha / Cl / Cm -6.17 -0.484 -0.0347 -4.69 -0.356 -0.0315 -3.91 -0.286 -0.0304 -2.74 -0.155 -0.0345 -1.64 -0.008 -0.0439 -0.86 0.083 -0.0455 0.29 0.219 -0.0461 1.46 0.346 -0.0455 2.37 0.434 -0.0441 3.65 0.562 -0.0419 4.53 0.646 -0.0410 5.39 0.727 -0.0399 6.65 0.840 -0.0376 7.47 0.912 -0.0362 8.67 1.009 -0.0331 9.43 1.063 -0.0305 10.56 1.117 -0.0249 11.64 1.131 -0.0217 12.38 1.133 -0.0817 13.50 1.123 -0.1102 14.57 1.108 -0.1267 15.49 1.053 -0.1340 16.46 0.994 -0.1389 17.44 0.983 -0.1379 18.30 1.010 -0.1426 16.79 0.995 -0.1399 15.83 1.005 -0.1384 14.90 1.063 -0.1340 13.67 1.146 -0.1146 12.74 1.153 -0.0916 11.74 1.142 -0.0224 10.57 1.126 -0.0229 9.95 1.098 -0.0252 8.67 1.016 -0.0301 7.68 0.936 -0.0328 6.65 0.847 -0.0350 5.91 0.779 -0.0364 4.79 0.677 -0.0387 3.63 0.573 -0.0403 2.79 0.485 -0.0419 1.58 0.351 -0.0451 0.28 0.216 -0.0463 -0.54 0.115 -0.0449 -1.73 -0.022 -0.0436 -2.52 -0.128 -0.0361 -3.69 -0.272 -0.0295 -4.53 -0.349 -0.0301 -5.78 -0.452 -0.0352 -6.63 -0.531 -0.0316 Tabulated from data in file AB01063.DAT & reduced using program Q06.01L File RG14.LFT created on 10-24-1997 at 19:34:41 using program FORMAT :::::::::::::: RG15C15.LFT :::::::::::::: Airfoil: RG15 (C) Builder: B. Champine Comment: flap = 15 degs Number of Reynolds #'s: 2 Average Reynolds #: 100300 Number of angles of attack: 49 alpha / Cl / Cm -6.32 0.124 -0.1373 -4.75 0.299 -0.1442 -4.17 0.345 -0.1401 -2.66 0.437 -0.1233 -2.09 0.505 -0.1252 -1.05 0.609 -0.1257 -0.04 0.694 -0.1247 1.45 0.915 -0.1430 2.01 1.016 -0.1494 3.50 1.106 -0.1315 4.03 1.124 -0.1256 5.07 1.158 -0.1155 6.06 1.212 -0.1086 7.09 1.270 -0.1015 8.09 1.322 -0.0957 9.56 1.390 -0.1127 10.06 1.371 -0.1376 11.44 1.292 -0.1989 12.35 1.183 -0.2044 13.36 1.178 -0.2109 14.35 1.177 -0.2143 15.37 1.149 -0.2123 16.44 1.169 -0.2194 17.49 1.190 -0.2263 18.04 1.235 -0.2360 16.20 1.143 -0.2183 15.28 1.144 -0.2180 14.30 1.152 -0.2160 13.36 1.186 -0.2181 12.47 1.230 -0.2159 11.16 1.284 -0.1972 10.29 1.331 -0.1610 9.45 1.344 -0.1154 8.61 1.342 -0.1019 7.25 1.284 -0.1058 6.32 1.232 -0.1121 5.38 1.189 -0.1202 4.47 1.143 -0.1254 3.50 1.108 -0.1368 2.13 1.038 -0.1543 1.15 0.859 -0.1427 0.25 0.743 -0.1309 -0.65 0.667 -0.1288 -1.60 0.588 -0.1318 -2.93 0.439 -0.1288 -3.85 0.386 -0.1402 -4.80 0.311 -0.1485 -5.79 0.218 -0.1496 -6.80 0.055 -0.1353 Tabulated from data in file MS01738.DAT & reduced using program Q06.01L Average Reynolds #: 200300 Number of angles of attack: 49 alpha / Cl / Cm -6.25 0.104 -0.1359 -5.12 0.238 -0.1444 -3.99 0.352 -0.1453 -2.81 0.446 -0.1365 -1.68 0.547 -0.1327 -1.05 0.599 -0.1307 0.03 0.788 -0.1467 1.16 1.015 -0.1609 2.26 1.037 -0.1405 3.39 1.063 -0.1253 4.45 1.125 -0.1180 5.04 1.159 -0.1147 6.10 1.225 -0.1086 7.17 1.287 -0.1031 8.16 1.333 -0.0981 9.19 1.392 -0.0984 10.46 1.372 -0.1564 11.27 1.339 -0.1940 12.14 1.329 -0.2097 13.53 1.281 -0.2209 13.99 1.275 -0.2231 15.43 1.270 -0.2210 16.32 1.286 -0.2254 17.20 1.292 -0.2298 18.47 1.254 -0.2455 15.98 1.260 -0.2238 15.45 1.281 -0.2268 14.41 1.266 -0.2226 12.94 1.306 -0.2176 12.38 1.308 -0.2165 11.48 1.343 -0.1976 10.10 1.406 -0.1494 9.62 1.368 -0.1264 8.27 1.339 -0.0986 7.35 1.298 -0.1035 6.36 1.242 -0.1092 5.37 1.182 -0.1149 4.35 1.123 -0.1209 3.26 1.061 -0.1275 2.15 1.049 -0.1433 1.46 1.043 -0.1569 0.34 0.872 -0.1549 -0.74 0.646 -0.1340 -1.77 0.538 -0.1327 -2.89 0.435 -0.1367 -4.13 0.339 -0.1465 -4.76 0.277 -0.1464 -5.93 0.138 -0.1377 -7.12 -0.004 -0.1304 Tabulated from data in file MS01737.DAT & reduced using program Q06.01L File RG15C15.LFT created on 10-24-1997 at 19:34:41 using program FORMAT :::::::::::::: RG15C20.LFT :::::::::::::: Airfoil: RG15 (C) Builder: B. Champine Comment: flap = 20 degs Number of Reynolds #'s: 2 Average Reynolds #: 100400 Number of angles of attack: 49 alpha / Cl / Cm -6.32 0.233 -0.1672 -4.78 0.375 -0.1630 -4.21 0.414 -0.1560 -2.68 0.538 -0.1485 -2.10 0.590 -0.1468 -1.07 0.702 -0.1485 0.39 0.817 -0.1487 0.97 0.873 -0.1535 2.02 1.040 -0.1596 3.06 1.052 -0.1398 4.11 1.117 -0.1321 5.16 1.179 -0.1265 6.20 1.239 -0.1202 7.23 1.304 -0.1151 8.24 1.360 -0.1112 9.23 1.406 -0.1371 10.17 1.382 -0.1789 11.07 1.296 -0.2184 12.08 1.303 -0.2395 13.53 1.223 -0.2420 14.09 1.191 -0.2401 15.14 1.179 -0.2390 16.21 1.213 -0.2482 17.23 1.219 -0.2535 18.29 1.235 -0.2591 16.38 1.207 -0.2539 15.38 1.226 -0.2514 14.43 1.176 -0.2411 13.46 1.210 -0.2417 12.51 1.210 -0.2394 11.13 1.281 -0.2259 10.30 1.377 -0.1980 9.42 1.430 -0.1598 8.55 1.380 -0.1153 7.22 1.307 -0.1168 6.28 1.247 -0.1217 5.34 1.194 -0.1271 4.39 1.133 -0.1318 3.41 1.071 -0.1365 2.45 1.048 -0.1515 1.47 0.982 -0.1665 0.07 0.807 -0.1495 -0.82 0.731 -0.1486 -1.75 0.630 -0.1488 -2.66 0.536 -0.1452 -4.02 0.427 -0.1530 -4.97 0.359 -0.1621 -5.95 0.271 -0.1662 -6.95 0.152 -0.1607 Tabulated from data in file MS01739.DAT & reduced using program Q06.01L Average Reynolds #: 199900 Number of angles of attack: 49 alpha / Cl / Cm -6.44 0.211 -0.1589 -4.84 0.379 -0.1643 -3.75 0.489 -0.1627 -3.17 0.548 -0.1609 -1.55 0.703 -0.1571 -0.95 0.740 -0.1522 0.20 0.920 -0.1641 1.28 1.031 -0.1588 2.38 1.047 -0.1404 3.04 1.091 -0.1361 4.13 1.163 -0.1306 5.26 1.241 -0.1257 6.33 1.306 -0.1205 7.40 1.365 -0.1153 8.38 1.412 -0.1112 9.30 1.458 -0.1523 10.57 1.439 -0.2021 11.01 1.428 -0.2182 12.32 1.342 -0.2356 13.19 1.323 -0.2424 14.51 1.312 -0.2410 15.42 1.347 -0.2468 16.31 1.289 -0.2542 17.20 1.380 -0.2567 18.05 1.304 -0.2663 16.12 1.253 -0.2533 15.65 1.355 -0.2499 14.14 1.315 -0.2438 13.12 1.348 -0.2454 12.16 1.329 -0.2365 11.64 1.389 -0.2322 10.27 1.446 -0.1978 9.38 1.450 -0.1515 8.53 1.427 -0.1138 7.14 1.361 -0.1194 6.57 1.330 -0.1224 5.52 1.264 -0.1274 4.49 1.196 -0.1322 3.39 1.120 -0.1372 2.27 1.045 -0.1439 1.08 1.035 -0.1667 0.40 0.965 -0.1701 -0.67 0.761 -0.1513 -1.77 0.694 -0.1604 -2.84 0.583 -0.1620 -3.94 0.474 -0.1656 -5.06 0.358 -0.1666 -5.67 0.299 -0.1660 -6.81 0.177 -0.1603 Tabulated from data in file MS01740.DAT & reduced using program Q06.01L File RG15C20.LFT created on 10-24-1997 at 19:34:41 using program FORMAT :::::::::::::: RG15C25.LFT :::::::::::::: Airfoil: RG15 (C) Builder: B. Champine Comment: flap = 25 degs Number of Reynolds #'s: 2 Average Reynolds #: 100200 Number of angles of attack: 49 alpha / Cl / Cm -6.30 0.378 -0.1859 -4.78 0.475 -0.1711 -3.75 0.536 -0.1606 -3.17 0.608 -0.1641 -1.67 0.749 -0.1646 -1.13 0.808 -0.1674 0.35 0.912 -0.1617 0.88 0.960 -0.1661 2.45 1.115 -0.1546 3.06 1.155 -0.1491 4.14 1.244 -0.1435 5.19 1.315 -0.1380 6.25 1.391 -0.1319 7.30 1.454 -0.1265 8.31 1.525 -0.1293 9.29 1.511 -0.1780 10.24 1.482 -0.2228 11.15 1.371 -0.2436 12.15 1.339 -0.2547 13.13 1.324 -0.2568 14.14 1.263 -0.2569 15.21 1.312 -0.2640 16.28 1.363 -0.2744 17.30 1.370 -0.2813 18.39 1.443 -0.2957 16.43 1.329 -0.2723 15.42 1.330 -0.2686 14.47 1.299 -0.2606 13.49 1.290 -0.2584 12.53 1.336 -0.2586 11.15 1.403 -0.2485 10.29 1.504 -0.2365 9.39 1.549 -0.1879 8.48 1.531 -0.1348 7.59 1.470 -0.1290 6.17 1.382 -0.1348 5.22 1.318 -0.1403 4.26 1.249 -0.1457 3.29 1.174 -0.1502 2.31 1.110 -0.1589 1.37 1.047 -0.1729 0.40 0.919 -0.1651 -0.95 0.825 -0.1673 -1.84 0.737 -0.1678 -2.80 0.642 -0.1664 -3.76 0.542 -0.1644 -4.72 0.474 -0.1707 -5.70 0.428 -0.1855 -7.19 0.273 -0.1805 Tabulated from data in file MS01741.DAT & reduced using program Q06.01L Average Reynolds #: 199600 Number of angles of attack: 49 alpha / Cl / Cm -6.47 0.356 -0.1895 -4.87 0.507 -0.1891 -3.84 0.596 -0.1842 -2.84 0.690 -0.1801 -1.77 0.793 -0.1776 -0.73 0.866 -0.1695 0.36 1.015 -0.1760 0.97 1.052 -0.1681 2.12 1.136 -0.1619 3.21 1.205 -0.1544 4.25 1.260 -0.1463 5.34 1.332 -0.1408 6.37 1.391 -0.1341 7.38 1.440 -0.1281 8.42 1.516 -0.1406 9.24 1.499 -0.1915 10.54 1.452 -0.2321 10.98 1.437 -0.2453 12.33 1.370 -0.2582 13.16 1.365 -0.2598 14.06 1.345 -0.2634 15.41 1.419 -0.2717 16.24 1.286 -0.2703 17.04 1.355 -0.2857 18.32 1.378 -0.2918 16.43 1.298 -0.2746 15.46 1.283 -0.2716 14.01 1.263 -0.2661 13.49 1.265 -0.2637 12.07 1.384 -0.2564 11.57 1.389 -0.2546 10.18 1.486 -0.2260 9.28 1.525 -0.1905 8.38 1.512 -0.1439 7.40 1.454 -0.1313 6.36 1.401 -0.1370 5.27 1.336 -0.1433 3.66 1.234 -0.1534 4.25 1.271 -0.1486 2.01 1.131 -0.1658 1.34 1.071 -0.1680 0.16 0.977 -0.1771 -0.99 0.855 -0.1749 -2.07 0.763 -0.1795 -2.69 0.706 -0.1817 -3.74 0.605 -0.1853 -4.85 0.509 -0.1908 -5.97 0.405 -0.1928 -7.09 0.273 -0.1847 Tabulated from data in file MS01742.DAT & reduced using program Q06.01L File RG15C25.LFT created on 10-24-1997 at 19:34:41 using program FORMAT :::::::::::::: RG15CF2.LFT :::::::::::::: Airfoil: RG15 (C) Builder: B. Champine Comment: flap = 2.5 degs Number of Reynolds #'s: 4 Average Reynolds #: 60038 Number of angles of attack: 57 alpha / Cl / Cm -8.99 -0.423 -0.0067 -8.08 -0.385 -0.0397 -7.04 -0.314 -0.0541 -6.09 -0.250 -0.0547 -5.03 -0.172 -0.0536 -3.71 -0.086 -0.0494 -2.97 -0.044 -0.0431 -1.96 0.049 -0.0509 -1.02 0.133 -0.0550 0.15 0.232 -0.0606 1.02 0.353 -0.0733 2.20 0.538 -0.0910 3.29 0.643 -0.0880 4.22 0.718 -0.0821 5.23 0.800 -0.0720 6.18 0.862 -0.0654 7.25 0.928 -0.0608 8.29 0.974 -0.0540 9.25 1.011 -0.0496 10.17 1.036 -0.0490 11.17 1.006 -0.0903 12.13 0.958 -0.1389 13.09 0.892 -0.1554 14.14 0.905 -0.1574 15.07 0.931 -0.1631 16.20 0.902 -0.1568 17.07 0.959 -0.1604 18.12 0.927 -0.1629 19.26 0.959 -0.1690 18.63 0.923 -0.1744 17.58 0.899 -0.1628 16.58 0.927 -0.1585 15.61 0.925 -0.1696 14.56 0.893 -0.1563 13.60 0.924 -0.1540 12.57 0.927 -0.1437 11.68 1.094 -0.1392 10.70 1.040 -0.0597 9.74 1.034 -0.0498 8.72 1.004 -0.0541 7.75 0.961 -0.0599 6.69 0.905 -0.0669 5.68 0.848 -0.0744 4.63 0.767 -0.0807 3.61 0.688 -0.0897 2.49 0.589 -0.0975 1.57 0.464 -0.0910 0.53 0.295 -0.0674 -0.58 0.196 -0.0554 -1.50 0.115 -0.0534 -2.52 0.021 -0.0453 -3.56 -0.052 -0.0486 -4.63 -0.116 -0.0548 -5.56 -0.188 -0.0525 -6.60 -0.268 -0.0525 -7.71 -0.350 -0.0455 -8.58 -0.412 -0.0157 Tabulated from data in file cl02373.dat & reduced using program C06.01 Average Reynolds #: 99938 Number of angles of attack: 57 alpha / Cl / Cm -8.98 -0.547 0.0135 -7.94 -0.504 -0.0286 -6.99 -0.398 -0.0547 -6.04 -0.304 -0.0552 -4.88 -0.194 -0.0552 -3.81 -0.085 -0.0583 -2.98 -0.023 -0.0523 -1.97 0.063 -0.0523 -0.94 0.166 -0.0573 0.03 0.310 -0.0747 1.06 0.455 -0.0852 2.21 0.554 -0.0755 3.17 0.667 -0.0783 4.16 0.755 -0.0731 5.19 0.844 -0.0692 6.32 0.941 -0.0652 7.18 0.981 -0.0587 8.27 1.023 -0.0516 9.31 1.063 -0.0458 10.28 1.084 -0.0426 11.22 1.044 -0.0677 12.10 1.060 -0.1493 13.25 1.012 -0.1590 14.16 0.936 -0.1632 15.26 0.931 -0.1663 16.24 0.964 -0.1594 17.10 0.928 -0.1675 18.19 0.960 -0.1725 19.18 0.986 -0.1778 18.63 0.976 -0.1728 17.55 0.964 -0.1772 16.60 0.990 -0.1756 15.61 0.946 -0.1657 14.58 0.952 -0.1626 13.60 0.937 -0.1653 12.61 0.969 -0.1663 11.67 1.081 -0.1386 10.69 1.156 -0.0903 9.72 1.073 -0.0438 8.72 1.048 -0.0496 7.73 1.004 -0.0554 6.70 0.964 -0.0627 5.72 0.906 -0.0685 4.63 0.813 -0.0714 3.64 0.725 -0.0762 2.58 0.611 -0.0805 1.55 0.510 -0.0845 0.57 0.399 -0.0854 -0.48 0.225 -0.0667 -1.47 0.113 -0.0550 -2.54 0.013 -0.0501 -3.60 -0.067 -0.0543 -4.54 -0.153 -0.0549 -5.61 -0.259 -0.0530 -6.67 -0.359 -0.0527 -7.64 -0.458 -0.0437 -8.62 -0.530 -0.0007 Tabulated from data in file cl02375.dat & reduced using program C06.01 Average Reynolds #: 199782 Number of angles of attack: 57 alpha / Cl / Cm -8.88 -0.524 -0.0004 -7.98 -0.438 -0.0473 -6.90 -0.309 -0.0709 -5.88 -0.222 -0.0693 -4.83 -0.122 -0.0691 -3.95 -0.037 -0.0703 -2.85 0.089 -0.0759 -1.85 0.206 -0.0796 -0.85 0.329 -0.0803 0.59 0.478 -0.0800 1.14 0.540 -0.0798 2.26 0.651 -0.0768 3.29 0.751 -0.0739 4.29 0.838 -0.0708 5.24 0.916 -0.0676 6.31 0.986 -0.0622 7.35 1.049 -0.0561 8.35 1.099 -0.0499 9.28 1.133 -0.0437 10.28 1.155 -0.0397 11.30 1.171 -0.1049 12.40 1.133 -0.1467 13.31 1.120 -0.1551 14.35 1.120 -0.1650 15.26 1.059 -0.1597 16.27 1.081 -0.1654 17.34 1.108 -0.1675 18.31 1.038 -0.1687 19.39 1.034 -0.1742 18.41 1.000 -0.1814 17.48 1.093 -0.1714 16.48 1.082 -0.1699 15.44 1.100 -0.1711 14.42 1.147 -0.1651 13.54 1.141 -0.1588 12.54 1.143 -0.1454 11.63 1.181 -0.1261 10.76 1.169 -0.0692 9.78 1.151 -0.0408 8.74 1.124 -0.0464 7.73 1.074 -0.0532 6.74 1.023 -0.0593 5.69 0.953 -0.0649 4.70 0.877 -0.0687 3.63 0.783 -0.0715 2.59 0.679 -0.0736 1.49 0.567 -0.0762 0.57 0.472 -0.0780 -0.67 0.341 -0.0790 -1.52 0.248 -0.0797 -2.54 0.124 -0.0750 -3.60 -0.002 -0.0707 -4.61 -0.102 -0.0681 -5.62 -0.201 -0.0676 -6.85 -0.305 -0.0707 -7.69 -0.402 -0.0591 -8.79 -0.521 -0.0055 Tabulated from data in file cl02377.dat & reduced using program C06.01 Average Reynolds #: 299742 Number of angles of attack: 59 alpha / Cl / Cm -8.86 -0.522 -0.0155 -8.02 -0.420 -0.0603 -7.04 -0.297 -0.0799 -6.08 -0.192 -0.0821 -5.07 -0.090 -0.0829 -4.00 0.017 -0.0843 -3.00 0.124 -0.0875 -1.89 0.242 -0.0862 -0.31 0.395 -0.0786 0.53 0.482 -0.0770 1.21 0.555 -0.0763 2.39 0.674 -0.0748 3.34 0.766 -0.0730 4.36 0.863 -0.0708 5.40 0.953 -0.0671 6.37 1.023 -0.0622 7.50 1.093 -0.0555 8.46 1.140 -0.0496 9.46 1.170 -0.0428 10.51 1.206 -0.0499 11.06 1.225 -0.0886 12.17 1.195 -0.1283 13.20 1.153 -0.1587 14.18 1.149 -0.1663 15.07 1.115 -0.1682 16.15 1.078 -0.1664 17.19 1.119 -0.1747 18.06 1.133 -0.1744 19.01 1.083 -0.1881 20.00 1.080 -0.2030 19.51 1.088 -0.1980 18.66 1.073 -0.1911 17.67 1.026 -0.1793 16.54 0.965 -0.1665 15.63 0.981 -0.1658 14.64 0.990 -0.1631 13.58 1.118 -0.1650 12.66 1.169 -0.1456 11.46 1.213 -0.0933 10.77 1.212 -0.0615 9.79 1.178 -0.0408 8.76 1.156 -0.0458 7.74 1.111 -0.0524 6.66 1.047 -0.0587 5.53 0.968 -0.0649 4.46 0.876 -0.0690 3.44 0.781 -0.0717 2.36 0.676 -0.0740 1.15 0.552 -0.0757 0.35 0.468 -0.0770 -0.91 0.341 -0.0804 -1.84 0.248 -0.0852 -2.74 0.157 -0.0876 -4.03 0.011 -0.0833 -5.01 -0.084 -0.0823 -6.16 -0.203 -0.0808 -6.78 -0.266 -0.0801 -7.91 -0.402 -0.0671 -8.79 -0.525 -0.0182 Tabulated from data in file pg02379.dat & reduced using program C06.01 File rg15cf2.lft created using program C06.01 on Mon Feb 02 15:11:35 1998 :::::::::::::: S6063.LFT :::::::::::::: Airfoil: S6063 Builder: R. Cavazos Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60200 Number of angles of attack: 49 alpha / Cl / Cm -5.84 -0.548 -0.0223 -4.42 -0.440 -0.0183 -3.56 -0.367 -0.0190 -2.59 -0.269 -0.0191 -1.26 -0.115 -0.0193 -0.33 -0.054 -0.0146 0.51 0.004 -0.0099 1.85 0.123 -0.0101 2.75 0.274 -0.0213 3.66 0.442 -0.0354 4.57 0.512 -0.0263 5.96 0.615 -0.0130 6.86 0.674 -0.0098 7.76 0.739 -0.0058 8.67 0.805 -0.0033 9.98 0.889 -0.0049 10.81 0.917 -0.0339 11.70 0.909 -0.0650 13.03 0.880 -0.0958 13.85 0.874 -0.1035 14.71 0.846 -0.1026 16.08 0.898 -0.1146 16.96 0.891 -0.1130 17.86 0.900 -0.1127 18.76 0.905 -0.1114 16.73 0.862 -0.1023 15.94 0.860 -0.1054 15.13 0.858 -0.0992 13.91 0.869 -0.0981 13.15 0.868 -0.0966 12.00 0.908 -0.0757 11.19 0.929 -0.0554 10.09 0.899 -0.0195 8.90 0.835 -0.0068 8.14 0.787 -0.0098 6.97 0.700 -0.0113 6.18 0.651 -0.0157 4.99 0.564 -0.0229 3.80 0.476 -0.0345 3.00 0.344 -0.0312 1.82 0.152 -0.0148 0.71 0.045 -0.0121 -0.04 -0.015 -0.0142 -1.15 -0.087 -0.0190 -2.29 -0.220 -0.0184 -3.38 -0.329 -0.0178 -4.13 -0.386 -0.0189 -5.36 -0.483 -0.0195 -6.17 -0.548 -0.0162 Tabulated from data in file CL01688.DAT & reduced using program Q06.01L Average Reynolds #: 100500 Number of angles of attack: 49 alpha / Cl / Cm -5.73 -0.452 -0.0201 -4.39 -0.337 -0.0187 -3.48 -0.262 -0.0177 -2.57 -0.191 -0.0159 -1.19 -0.060 -0.0178 -0.31 -0.015 -0.0137 0.55 0.042 -0.0107 1.47 0.178 -0.0185 2.94 0.396 -0.0290 3.92 0.481 -0.0230 4.89 0.553 -0.0153 5.82 0.631 -0.0114 6.82 0.712 -0.0088 7.79 0.774 -0.0052 8.76 0.841 -0.0028 9.67 0.904 -0.0084 10.93 0.929 -0.0653 11.78 0.898 -0.0869 12.68 0.897 -0.1017 14.09 0.877 -0.1104 15.00 0.864 -0.1089 15.98 0.866 -0.1106 16.88 0.862 -0.1100 17.80 0.879 -0.1119 18.73 0.884 -0.1109 17.11 0.871 -0.1119 15.82 0.876 -0.1123 14.99 0.885 -0.1153 14.17 0.899 -0.1150 12.88 0.903 -0.1078 12.09 0.904 -0.0998 10.90 0.923 -0.0667 10.16 0.924 -0.0343 9.05 0.859 -0.0082 7.91 0.791 -0.0089 7.08 0.732 -0.0110 5.87 0.641 -0.0142 5.07 0.583 -0.0172 3.88 0.489 -0.0251 3.07 0.421 -0.0318 1.88 0.264 -0.0300 0.71 0.068 -0.0125 -0.05 0.008 -0.0131 -1.25 -0.060 -0.0194 -2.03 -0.156 -0.0157 -3.17 -0.240 -0.0163 -4.39 -0.331 -0.0175 -5.18 -0.396 -0.0190 -6.39 -0.516 -0.0071 Tabulated from data in file AB01690.DAT & reduced using program Q06.01L Average Reynolds #: 201100 Number of angles of attack: 49 alpha / Cl / Cm -5.79 -0.510 -0.0151 -4.34 -0.379 -0.0158 -3.34 -0.288 -0.0149 -2.40 -0.203 -0.0130 -1.48 -0.133 -0.0100 -0.55 -0.015 -0.0161 0.92 0.160 -0.0220 1.85 0.264 -0.0218 2.78 0.357 -0.0201 3.90 0.443 -0.0170 4.83 0.521 -0.0143 5.76 0.592 -0.0122 6.68 0.665 -0.0100 7.94 0.766 -0.0067 8.65 0.834 -0.0045 9.89 0.919 -0.0291 10.77 0.948 -0.0630 12.11 0.948 -0.0973 13.04 0.921 -0.1123 13.97 0.903 -0.1166 14.87 0.883 -0.1177 15.90 0.865 -0.1167 16.86 0.860 -0.1162 17.81 0.879 -0.1184 18.88 0.896 -0.1206 17.02 0.863 -0.1176 16.00 0.868 -0.1167 14.99 0.887 -0.1177 14.04 0.868 -0.1151 13.11 0.900 -0.1152 11.79 0.934 -0.0950 10.93 0.948 -0.0682 10.14 0.933 -0.0372 9.03 0.871 -0.0068 7.93 0.779 -0.0081 6.87 0.689 -0.0108 6.11 0.626 -0.0123 4.91 0.530 -0.0144 3.71 0.429 -0.0177 2.88 0.359 -0.0194 1.95 0.279 -0.0215 0.76 0.151 -0.0207 -0.04 0.057 -0.0186 -1.21 -0.089 -0.0090 -2.37 -0.192 -0.0107 -3.24 -0.272 -0.0118 -4.48 -0.388 -0.0123 -5.32 -0.458 -0.0133 -6.25 -0.550 -0.0084 Tabulated from data in file AB01692.DAT & reduced using program Q06.01L Average Reynolds #: 302000 Number of angles of attack: 49 alpha / Cl / Cm -5.68 -0.516 -0.0149 -4.17 -0.377 -0.0147 -3.62 -0.326 -0.0139 -2.20 -0.193 -0.0121 -1.15 -0.084 -0.0142 -0.55 -0.005 -0.0181 0.51 0.128 -0.0233 1.70 0.225 -0.0209 2.68 0.324 -0.0189 3.98 0.469 -0.0165 4.93 0.550 -0.0149 5.88 0.632 -0.0131 6.81 0.710 -0.0108 7.70 0.780 -0.0085 8.93 0.878 -0.0061 9.70 0.922 -0.0184 10.82 0.968 -0.0576 11.95 0.974 -0.0893 12.43 0.963 -0.0991 13.73 0.961 -0.1140 15.00 0.935 -0.1197 15.89 0.922 -0.1206 16.70 0.878 -0.1187 17.99 0.896 -0.1213 18.83 0.890 -0.1187 16.83 0.885 -0.1202 15.78 0.878 -0.1208 14.85 0.936 -0.1197 13.88 0.925 -0.1168 12.93 0.961 -0.1058 12.11 0.974 -0.0907 11.00 0.978 -0.0623 10.23 0.954 -0.0363 9.15 0.894 -0.0079 8.03 0.807 -0.0082 6.79 0.709 -0.0112 6.00 0.644 -0.0132 5.15 0.571 -0.0148 3.87 0.460 -0.0166 3.01 0.379 -0.0182 1.96 0.252 -0.0204 0.48 0.126 -0.0233 -0.01 0.077 -0.0240 -1.30 -0.100 -0.0134 -2.19 -0.191 -0.0113 -3.07 -0.274 -0.0123 -4.37 -0.397 -0.0135 -5.37 -0.487 -0.0150 -6.33 -0.581 -0.0105 Tabulated from data in file AB01694.DAT & reduced using program Q06.01L File S6063.LFT created on 10-24-1997 at 19:34:41 using program FORMAT :::::::::::::: S7012B0T.LFT :::::::::::::: Airfoil: S7012 (B) Builder: M. Lachowski Comment: flap = 0 degs; Zig-Zag trip type "C" @ u.s. x/c=2% & l.s. x/c=5% (h = 0.023") Number of Reynolds #'s: 3 Average Reynolds #: 100600 Number of angles of attack: 49 alpha / Cl / Cm -5.56 -0.409 -0.0423 -4.58 -0.313 -0.0420 -3.14 -0.172 -0.0417 -2.17 -0.086 -0.0396 -1.19 -0.001 -0.0407 -0.21 0.133 -0.0510 0.77 0.240 -0.0541 1.71 0.313 -0.0465 2.66 0.386 -0.0413 4.05 0.515 -0.0406 5.02 0.602 -0.0396 6.03 0.696 -0.0399 7.03 0.786 -0.0389 8.03 0.870 -0.0377 8.98 0.951 -0.0364 9.91 1.024 -0.0340 10.80 1.066 -0.0320 12.10 1.038 -0.1069 13.02 0.878 -0.1354 13.97 0.899 -0.1410 14.96 0.928 -0.1476 15.96 0.931 -0.1515 17.00 0.963 -0.1589 18.04 0.962 -0.1585 19.05 0.949 -0.1600 16.78 0.936 -0.1560 16.22 0.950 -0.1557 14.89 0.928 -0.1497 13.94 0.881 -0.1414 13.02 0.882 -0.1349 12.16 0.928 -0.1259 10.96 1.066 -0.0392 10.15 1.043 -0.0383 8.95 0.951 -0.0392 8.08 0.878 -0.0416 7.18 0.801 -0.0429 5.88 0.686 -0.0437 4.99 0.604 -0.0458 4.11 0.517 -0.0452 2.87 0.411 -0.0467 1.97 0.332 -0.0491 1.09 0.273 -0.0602 -0.16 0.142 -0.0589 -1.05 0.019 -0.0460 -2.30 -0.089 -0.0449 -3.18 -0.168 -0.0461 -4.08 -0.256 -0.0458 -5.38 -0.380 -0.0440 -6.31 -0.476 -0.0411 Tabulated from data in file PG01781.DAT & reduced using program Q06.01L Average Reynolds #: 200900 Number of angles of attack: 49 alpha / Cl / Cm -5.61 -0.402 -0.0416 -4.14 -0.266 -0.0430 -3.54 -0.211 -0.0422 -2.50 -0.102 -0.0437 -1.06 0.075 -0.0519 -0.45 0.123 -0.0466 0.58 0.220 -0.0448 1.60 0.324 -0.0448 3.09 0.479 -0.0449 3.71 0.539 -0.0450 4.70 0.633 -0.0442 5.73 0.727 -0.0431 6.76 0.819 -0.0418 8.17 0.942 -0.0407 9.11 1.020 -0.0394 10.07 1.096 -0.0382 11.00 1.145 -0.0364 11.91 1.153 -0.0550 13.11 1.088 -0.1202 14.01 1.062 -0.1378 14.97 1.018 -0.1495 16.02 1.004 -0.1529 17.05 0.991 -0.1525 18.15 0.992 -0.1535 19.17 1.013 -0.1594 16.46 1.011 -0.1547 16.71 1.006 -0.1531 14.63 1.062 -0.1499 14.11 1.094 -0.1361 13.16 1.098 -0.1178 11.97 1.130 -0.0709 11.18 1.151 -0.0376 9.96 1.086 -0.0399 9.12 1.018 -0.0404 8.21 0.941 -0.0414 6.88 0.826 -0.0429 5.95 0.746 -0.0441 5.01 0.663 -0.0455 4.05 0.572 -0.0460 3.10 0.480 -0.0460 1.77 0.342 -0.0453 0.88 0.252 -0.0450 -0.05 0.161 -0.0460 -1.39 0.027 -0.0508 -2.31 -0.084 -0.0443 -3.26 -0.182 -0.0418 -4.21 -0.269 -0.0411 -5.18 -0.356 -0.0403 -6.57 -0.485 -0.0352 Tabulated from data in file PG01783.DAT & reduced using program Q06.01L Average Reynolds #: 302000 Number of angles of attack: 41 alpha / Cl / Cm -5.95 -0.446 -0.0397 -4.36 -0.297 -0.0433 -3.31 -0.182 -0.0456 -2.17 -0.054 -0.0471 -1.08 0.043 -0.0443 -0.42 0.112 -0.0447 0.71 0.228 -0.0450 1.81 0.344 -0.0453 2.90 0.457 -0.0458 3.97 0.565 -0.0459 5.02 0.666 -0.0458 6.05 0.763 -0.0453 7.07 0.853 -0.0446 8.08 0.940 -0.0428 9.07 1.027 -0.0417 10.03 1.102 -0.0402 10.99 1.147 -0.0376 11.88 1.145 -0.0490 12.70 1.143 -0.0772 13.89 1.151 -0.1293 15.03 1.072 -0.1506 13.00 1.130 -0.0898 12.20 1.146 -0.0606 11.09 1.151 -0.0398 10.20 1.112 -0.0416 9.29 1.045 -0.0433 7.99 0.931 -0.0447 7.03 0.850 -0.0460 6.05 0.762 -0.0468 5.05 0.667 -0.0471 4.07 0.570 -0.0470 3.08 0.472 -0.0468 1.63 0.320 -0.0465 1.03 0.257 -0.0463 -0.39 0.111 -0.0451 -1.00 0.049 -0.0449 -2.51 -0.090 -0.0486 -3.15 -0.168 -0.0459 -4.19 -0.284 -0.0428 -5.26 -0.387 -0.0402 -6.32 -0.481 -0.0400 Tabulated from data in file PG01786.DAT & reduced using program Q06.01L File S7012B0T.LFT created on 10-24-1997 at 19:34:41 using program FORMAT :::::::::::::: S7012B15.LFT :::::::::::::: Airfoil: S7012 (B) Builder: M. Lachowski Comment: flap = 15 degs Number of Reynolds #'s: 2 Average Reynolds #: 99800 Number of angles of attack: 49 alpha / Cl / Cm -5.57 0.195 -0.1606 -4.12 0.301 -0.1538 -3.54 0.333 -0.1466 -2.08 0.451 -0.1382 -1.51 0.506 -0.1368 -0.07 0.675 -0.1432 0.93 0.840 -0.1581 1.96 1.022 -0.1712 2.97 1.089 -0.1601 3.99 1.111 -0.1469 5.01 1.164 -0.1395 6.03 1.204 -0.1303 7.02 1.247 -0.1227 8.01 1.298 -0.1162 8.98 1.333 -0.1110 9.93 1.370 -0.1500 10.80 1.339 -0.1885 11.73 1.257 -0.2093 13.09 1.192 -0.2235 14.02 1.200 -0.2359 15.03 1.215 -0.2390 16.05 1.229 -0.2453 17.04 1.224 -0.2436 18.08 1.230 -0.2499 19.11 1.266 -0.2643 16.78 1.217 -0.2490 16.22 1.220 -0.2472 14.83 1.195 -0.2416 13.95 1.209 -0.2400 13.01 1.199 -0.2325 12.11 1.255 -0.2220 11.23 1.333 -0.2031 9.98 1.373 -0.1498 9.12 1.345 -0.1204 8.26 1.315 -0.1207 6.92 1.254 -0.1287 6.01 1.211 -0.1340 5.07 1.176 -0.1431 4.11 1.126 -0.1504 3.16 1.102 -0.1621 1.79 0.997 -0.1747 0.87 0.838 -0.1615 -0.06 0.693 -0.1478 -0.98 0.581 -0.1389 -2.32 0.438 -0.1398 -3.23 0.356 -0.1435 -4.17 0.294 -0.1508 -5.11 0.242 -0.1612 -6.09 0.147 -0.1601 Tabulated from data in file MS01731.DAT & reduced using program Q06.01L Average Reynolds #: 200000 Number of angles of attack: 49 alpha / Cl / Cm -5.74 0.174 -0.1544 -4.21 0.323 -0.1577 -3.15 0.422 -0.1561 -2.08 0.525 -0.1535 -1.05 0.624 -0.1514 -0.03 0.739 -0.1539 1.00 0.970 -0.1730 2.08 1.031 -0.1595 2.75 1.043 -0.1504 3.87 1.089 -0.1384 4.98 1.149 -0.1292 6.07 1.207 -0.1217 6.69 1.245 -0.1189 8.19 1.326 -0.1121 8.74 1.347 -0.1100 10.08 1.391 -0.1395 10.91 1.402 -0.1713 11.76 1.400 -0.2026 12.98 1.275 -0.2272 13.83 1.209 -0.2288 15.10 1.216 -0.2369 15.98 1.226 -0.2392 16.84 1.237 -0.2438 17.71 1.226 -0.2438 19.01 1.261 -0.2533 17.07 1.222 -0.2416 16.11 1.212 -0.2388 15.13 1.241 -0.2389 14.18 1.214 -0.2345 12.76 1.276 -0.2254 11.84 1.367 -0.2090 10.91 1.423 -0.1735 10.01 1.389 -0.1371 9.14 1.364 -0.1101 7.80 1.307 -0.1161 7.26 1.281 -0.1192 5.80 1.193 -0.1266 5.18 1.161 -0.1310 4.12 1.105 -0.1381 3.03 1.056 -0.1481 1.95 1.036 -0.1629 0.78 0.911 -0.1698 -0.30 0.688 -0.1495 -1.39 0.582 -0.1497 -2.04 0.517 -0.1513 -3.13 0.424 -0.1568 -4.25 0.314 -0.1582 -5.34 0.208 -0.1554 -6.44 0.098 -0.1493 Tabulated from data in file MS01732.DAT & reduced using program Q06.01L File S7012B15.LFT created on 10-24-1997 at 19:34:41 using program FORMAT :::::::::::::: S7012B20.LFT :::::::::::::: Airfoil: S7012 (B) Builder: M. Lachowski Comment: flap = 20 degs Number of Reynolds #'s: 2 Average Reynolds #: 99900 Number of angles of attack: 49 alpha / Cl / Cm -5.49 0.294 -0.1824 -4.46 0.374 -0.1760 -3.43 0.447 -0.1647 -2.42 0.541 -0.1623 -1.42 0.636 -0.1632 -0.42 0.729 -0.1620 0.60 0.834 -0.1673 2.08 1.042 -0.1762 2.66 1.057 -0.1662 3.68 1.096 -0.1549 4.72 1.167 -0.1487 5.76 1.227 -0.1426 6.78 1.284 -0.1358 7.80 1.333 -0.1318 8.78 1.377 -0.1296 9.73 1.398 -0.1731 11.08 1.357 -0.2273 11.99 1.271 -0.2419 12.91 1.225 -0.2488 13.91 1.220 -0.2570 14.94 1.228 -0.2577 15.93 1.236 -0.2613 16.99 1.277 -0.2708 18.04 1.305 -0.2763 19.08 1.319 -0.2877 16.76 1.266 -0.2702 16.18 1.259 -0.2687 15.20 1.241 -0.2647 13.82 1.234 -0.2600 12.90 1.219 -0.2503 11.97 1.250 -0.2455 11.05 1.332 -0.2367 10.20 1.413 -0.2042 8.89 1.390 -0.1376 8.03 1.347 -0.1352 7.10 1.302 -0.1376 6.14 1.252 -0.1431 5.18 1.199 -0.1486 3.78 1.104 -0.1560 2.84 1.069 -0.1670 1.89 1.048 -0.1847 0.93 0.871 -0.1724 0.00 0.778 -0.1658 -0.93 0.693 -0.1665 -2.26 0.563 -0.1655 -3.20 0.472 -0.1655 -4.15 0.400 -0.1743 -5.13 0.324 -0.1804 -6.11 0.240 -0.1792 Tabulated from data in file MS01734.DAT & reduced using program Q06.01L Average Reynolds #: 199700 Number of angles of attack: 49 alpha / Cl / Cm -5.76 0.265 -0.1739 -4.24 0.411 -0.1742 -3.23 0.501 -0.1713 -2.22 0.598 -0.1691 -1.18 0.695 -0.1658 -0.13 0.799 -0.1656 0.91 1.008 -0.1834 1.99 1.015 -0.1616 3.14 1.093 -0.1539 3.77 1.138 -0.1502 4.81 1.210 -0.1449 5.86 1.274 -0.1392 6.90 1.338 -0.1345 7.93 1.389 -0.1292 8.94 1.468 -0.1313 9.78 1.468 -0.1657 11.02 1.459 -0.2230 11.82 1.399 -0.2415 13.01 1.271 -0.2525 13.83 1.278 -0.2600 15.06 1.263 -0.2626 15.94 1.283 -0.2668 16.82 1.288 -0.2707 18.06 1.295 -0.2765 18.90 1.342 -0.2847 17.07 1.271 -0.2706 16.12 1.250 -0.2661 15.20 1.273 -0.2665 13.85 1.280 -0.2625 12.92 1.322 -0.2576 12.06 1.397 -0.2473 11.19 1.465 -0.2290 9.88 1.483 -0.1765 9.01 1.471 -0.1354 8.05 1.394 -0.1312 7.06 1.347 -0.1363 6.00 1.284 -0.1409 4.93 1.218 -0.1462 3.82 1.141 -0.1521 2.70 1.055 -0.1581 2.04 1.013 -0.1626 0.94 1.010 -0.1847 -0.12 0.806 -0.1672 -1.17 0.707 -0.1678 -2.26 0.597 -0.1696 -3.33 0.493 -0.1726 -4.45 0.390 -0.1747 -5.05 0.333 -0.1751 -6.17 0.218 -0.1718 Tabulated from data in file MS01733.DAT & reduced using program Q06.01L File S7012B20.LFT created on 10-24-1997 at 19:34:41 using program FORMAT :::::::::::::: S7012B25.LFT :::::::::::::: Airfoil: S7012 (B) Builder: M. Lachowski Comment: flap = 25 degs Number of Reynolds #'s: 2 Average Reynolds #: 100000 Number of angles of attack: 49 alpha / Cl / Cm -5.54 0.394 -0.1933 -4.08 0.503 -0.1796 -3.49 0.539 -0.1732 -2.46 0.641 -0.1736 -1.44 0.743 -0.1743 -0.41 0.841 -0.1799 0.59 0.932 -0.1784 1.62 1.081 -0.1854 2.63 1.122 -0.1715 3.66 1.185 -0.1632 4.70 1.251 -0.1589 5.74 1.303 -0.1530 6.77 1.354 -0.1471 7.77 1.403 -0.1440 8.76 1.462 -0.1483 9.72 1.464 -0.1961 11.05 1.344 -0.2499 12.01 1.281 -0.2563 12.95 1.298 -0.2680 13.96 1.301 -0.2760 14.99 1.329 -0.2823 15.97 1.317 -0.2846 17.03 1.371 -0.2957 18.08 1.352 -0.2970 19.08 1.373 -0.3101 16.66 1.314 -0.2856 16.14 1.345 -0.2910 15.14 1.313 -0.2824 14.17 1.307 -0.2781 12.79 1.285 -0.2689 11.91 1.306 -0.2634 10.99 1.339 -0.2528 10.09 1.449 -0.2263 9.22 1.462 -0.1852 7.86 1.404 -0.1498 6.98 1.362 -0.1494 6.03 1.317 -0.1534 5.06 1.267 -0.1582 4.09 1.219 -0.1646 3.12 1.161 -0.1717 1.76 1.090 -0.1859 1.17 1.023 -0.1888 -0.17 0.872 -0.1830 -1.10 0.774 -0.1808 -2.04 0.680 -0.1753 -3.41 0.547 -0.1766 -4.35 0.481 -0.1864 -5.32 0.409 -0.1956 -6.31 0.325 -0.1985 Tabulated from data in file MS01735.DAT & reduced using program Q06.01L Average Reynolds #: 199700 Number of angles of attack: 49 alpha / Cl / Cm -5.67 0.417 -0.2002 -4.15 0.553 -0.1976 -3.12 0.644 -0.1942 -2.12 0.731 -0.1887 -1.09 0.824 -0.1847 -0.03 0.900 -0.1795 1.03 1.020 -0.1786 1.62 1.066 -0.1749 2.66 1.163 -0.1725 4.21 1.276 -0.1647 4.85 1.306 -0.1586 5.89 1.364 -0.1524 6.93 1.421 -0.1469 7.98 1.465 -0.1407 8.91 1.541 -0.1621 9.76 1.524 -0.1995 11.01 1.478 -0.2421 11.82 1.430 -0.2629 13.02 1.327 -0.2703 13.85 1.335 -0.2761 14.69 1.329 -0.2789 15.92 1.374 -0.2884 16.73 1.357 -0.2875 18.02 1.388 -0.2973 18.83 1.415 -0.3054 17.00 1.348 -0.2884 16.09 1.345 -0.2850 15.13 1.331 -0.2803 13.79 1.320 -0.2758 12.90 1.322 -0.2697 12.01 1.375 -0.2617 11.12 1.425 -0.2480 10.24 1.532 -0.2149 8.87 1.538 -0.1609 7.90 1.465 -0.1424 6.89 1.424 -0.1482 5.80 1.364 -0.1544 5.15 1.327 -0.1585 4.07 1.270 -0.1672 2.95 1.188 -0.1727 1.87 1.090 -0.1752 0.77 1.009 -0.1823 -0.30 0.875 -0.1773 -0.92 0.845 -0.1837 -2.49 0.709 -0.1922 -3.05 0.663 -0.1957 -4.12 0.562 -0.1986 -5.18 0.465 -0.2011 -6.25 0.370 -0.2014 Tabulated from data in file MS01736.DAT & reduced using program Q06.01L File S7012B25.LFT created on 10-24-1997 at 19:34:41 using program FORMAT :::::::::::::: S7012BF2.LFT :::::::::::::: Airfoil: S7012 (B) Builder: M. Lachowski Comment: clean, flap = 2.5 degs Number of Reynolds #'s: 4 Average Reynolds #: 60028 Number of angles of attack: 53 alpha / Cl / Cm -6.17 -0.357 -0.0578 -5.17 -0.270 -0.0599 -4.12 -0.173 -0.0612 -3.08 -0.074 -0.0538 -2.06 -0.021 -0.0453 -1.05 0.103 -0.0552 -0.02 0.211 -0.0630 1.02 0.347 -0.0789 2.02 0.485 -0.0975 3.03 0.575 -0.0991 4.05 0.650 -0.0918 5.10 0.724 -0.0847 6.13 0.789 -0.0777 7.10 0.854 -0.0699 8.23 0.902 -0.0625 9.18 0.942 -0.0615 10.20 0.960 -0.0562 11.14 0.960 -0.0646 12.04 0.946 -0.1517 13.05 0.877 -0.1605 14.04 0.881 -0.1735 15.08 0.878 -0.1782 16.18 0.905 -0.1752 17.11 0.878 -0.1890 18.01 0.880 -0.1868 19.01 0.929 -0.1921 20.04 0.926 -0.2009 19.53 0.903 -0.2016 18.49 0.881 -0.1923 17.52 0.851 -0.1846 16.51 0.881 -0.1870 15.57 0.904 -0.1843 14.50 0.896 -0.1857 13.51 0.891 -0.1802 12.51 0.955 -0.1667 11.62 0.924 -0.1001 10.69 0.980 -0.0605 9.66 0.964 -0.0613 8.57 0.924 -0.0638 7.63 0.888 -0.0705 6.47 0.835 -0.0777 5.61 0.770 -0.0825 4.57 0.702 -0.0883 3.51 0.632 -0.0985 2.52 0.556 -0.1059 1.46 0.437 -0.0955 0.38 0.260 -0.0681 -0.52 0.175 -0.0600 -1.65 0.044 -0.0480 -2.58 -0.026 -0.0613 -3.59 -0.121 -0.0575 -4.66 -0.231 -0.0552 -5.65 -0.327 -0.0543 Tabulated from data in file cl02256.dat & reduced using program C06.01 Average Reynolds #: 99947 Number of angles of attack: 59 alpha / Cl / Cm -9.10 -0.633 0.0442 -8.12 -0.607 0.0060 -7.17 -0.491 -0.0502 -6.08 -0.384 -0.0605 -4.88 -0.266 -0.0631 -4.13 -0.178 -0.0650 -3.00 -0.058 -0.0628 -2.06 0.035 -0.0593 -1.01 0.114 -0.0571 -0.05 0.244 -0.0771 0.99 0.368 -0.0861 2.00 0.467 -0.0865 3.08 0.572 -0.0826 4.07 0.667 -0.0784 5.22 0.785 -0.0752 6.14 0.889 -0.0751 7.17 0.973 -0.0705 8.17 1.030 -0.0650 9.22 1.075 -0.0593 10.21 1.107 -0.0552 11.19 1.171 -0.0686 12.16 1.037 -0.1575 13.05 0.991 -0.1642 14.13 0.966 -0.1740 15.03 0.984 -0.1817 16.07 0.976 -0.1801 17.11 0.977 -0.1884 18.02 1.002 -0.1842 19.09 1.010 -0.1923 20.03 1.049 -0.2002 19.52 0.997 -0.2085 18.52 0.979 -0.1909 17.53 0.994 -0.1918 16.55 0.968 -0.1884 15.50 0.982 -0.1933 14.57 0.972 -0.1885 13.49 0.978 -0.1836 12.59 1.033 -0.1698 11.58 1.156 -0.1463 10.58 1.119 -0.0562 9.52 1.098 -0.0576 8.68 1.067 -0.0622 7.66 1.012 -0.0673 6.56 0.942 -0.0722 5.60 0.843 -0.0734 4.61 0.741 -0.0749 3.57 0.635 -0.0784 2.50 0.525 -0.0809 1.49 0.421 -0.0833 0.39 0.310 -0.0849 -0.51 0.175 -0.0653 -1.72 0.064 -0.0586 -2.66 -0.017 -0.0583 -3.68 -0.109 -0.0598 -4.65 -0.221 -0.0566 -5.60 -0.320 -0.0553 -6.64 -0.425 -0.0536 -7.69 -0.551 -0.0158 -8.70 -0.598 0.0323 Tabulated from data in file cl02258.dat & reduced using program C06.01 Average Reynolds #: 200031 Number of angles of attack: 43 alpha / Cl / Cm -9.19 -0.596 0.0373 -8.15 -0.529 -0.0065 -6.86 -0.353 -0.0707 -5.94 -0.266 -0.0748 -4.90 -0.158 -0.0782 -4.07 -0.067 -0.0817 -2.91 0.050 -0.0848 -1.97 0.156 -0.0874 -0.99 0.255 -0.0870 0.10 0.362 -0.0822 1.15 0.468 -0.0807 2.08 0.560 -0.0797 3.23 0.677 -0.0786 4.12 0.771 -0.0779 5.17 0.872 -0.0768 6.33 0.978 -0.0743 7.17 1.042 -0.0710 8.19 1.109 -0.0663 9.20 1.146 -0.0601 10.31 1.170 -0.0553 11.16 1.163 -0.0929 12.10 1.146 -0.1411 11.67 1.217 -0.1204 10.86 1.190 -0.0815 9.63 1.164 -0.0589 8.75 1.141 -0.0641 7.74 1.087 -0.0693 6.62 1.009 -0.0740 5.66 0.927 -0.0764 4.65 0.822 -0.0764 3.56 0.704 -0.0768 2.59 0.604 -0.0773 1.56 0.501 -0.0782 0.51 0.394 -0.0797 -0.49 0.304 -0.0831 -1.52 0.195 -0.0852 -2.79 0.058 -0.0835 -3.58 -0.019 -0.0829 -4.62 -0.131 -0.0781 -5.66 -0.236 -0.0745 -6.67 -0.338 -0.0701 -7.70 -0.474 -0.0415 -8.60 -0.574 0.0138 Tabulated from data in file cl02260.dat & reduced using program C06.01 Average Reynolds #: 300168 Number of angles of attack: 55 alpha / Cl / Cm -9.20 -0.598 0.0315 -8.17 -0.537 -0.0199 -7.21 -0.391 -0.0715 -6.17 -0.284 -0.0769 -5.03 -0.166 -0.0811 -4.14 -0.071 -0.0843 -3.11 0.038 -0.0868 -1.80 0.176 -0.0884 -1.06 0.249 -0.0857 0.09 0.357 -0.0792 1.03 0.449 -0.0770 2.02 0.558 -0.0773 3.09 0.673 -0.0782 4.09 0.779 -0.0780 5.11 0.881 -0.0773 6.15 0.976 -0.0757 7.24 1.063 -0.0726 8.28 1.135 -0.0684 9.20 1.171 -0.0624 10.20 1.189 -0.0572 11.22 1.231 -0.0759 11.98 1.236 -0.1278 13.15 1.218 -0.1634 14.08 1.196 -0.1806 15.07 1.081 -0.1854 15.98 1.032 -0.1881 17.04 0.986 -0.1870 18.07 0.999 -0.1901 17.62 0.983 -0.1931 16.63 0.993 -0.1887 15.64 1.000 -0.1887 14.56 1.034 -0.1842 13.68 1.117 -0.1759 12.74 1.194 -0.1529 11.67 1.223 -0.1032 10.66 1.207 -0.0569 9.70 1.183 -0.0582 8.69 1.154 -0.0637 7.50 1.086 -0.0693 6.64 1.020 -0.0726 5.54 0.927 -0.0753 4.56 0.830 -0.0763 3.48 0.718 -0.0769 2.41 0.601 -0.0766 1.39 0.493 -0.0762 0.13 0.359 -0.0780 -0.65 0.287 -0.0821 -1.67 0.187 -0.0874 -2.67 0.081 -0.0872 -3.94 -0.055 -0.0834 -4.64 -0.129 -0.0803 -6.04 -0.274 -0.0759 -6.91 -0.360 -0.0723 -7.75 -0.476 -0.0430 -8.64 -0.576 0.0080 Tabulated from data in file cl02262.dat & reduced using program C06.01 File s7012bf2.lft created using program C06.01 on Mon Feb 02 15:11:35 1998 :::::::::::::: S7075A0.LFT :::::::::::::: Airfoil: S7075 (A) Builder: J. Robertson Comment: flap = 0 degs: clean Number of Reynolds #'s: 4 Average Reynolds #: 60200 Number of angles of attack: 49 alpha / Cl / Cm -5.99 -0.306 -0.0399 -4.73 -0.217 -0.0468 -3.74 -0.148 -0.0483 -2.83 -0.081 -0.0445 -1.54 0.023 -0.0479 -0.57 0.122 -0.0481 0.37 0.223 -0.0544 1.36 0.333 -0.0597 2.38 0.451 -0.0674 3.42 0.613 -0.0779 4.47 0.774 -0.0797 5.72 0.885 -0.0706 6.68 0.966 -0.0650 7.60 1.020 -0.0616 8.50 1.082 -0.0589 9.68 1.128 -0.0503 10.61 1.148 -0.0466 11.54 1.163 -0.0477 12.67 0.960 -0.0993 13.57 0.930 -0.1095 14.52 0.973 -0.1263 15.75 0.930 -0.1261 16.44 0.997 -0.1356 17.67 1.009 -0.1408 18.66 1.004 -0.1388 16.97 1.020 -0.1432 15.83 0.945 -0.1334 14.98 0.976 -0.1311 13.85 0.980 -0.1201 13.04 0.995 -0.1143 12.01 1.156 -0.0784 10.97 1.184 -0.0551 9.96 1.158 -0.0527 9.17 1.147 -0.0568 8.09 1.084 -0.0637 7.01 1.006 -0.0694 5.89 0.922 -0.0775 5.09 0.852 -0.0806 3.93 0.725 -0.0887 2.77 0.549 -0.0818 1.91 0.407 -0.0721 0.76 0.273 -0.0603 -0.28 0.171 -0.0547 -1.32 0.077 -0.0512 -2.35 -0.009 -0.0517 -3.39 -0.098 -0.0514 -4.43 -0.182 -0.0507 -5.22 -0.244 -0.0491 -6.39 -0.346 -0.0372 Tabulated from data in file CL01325.DAT & reduced using program Q06.01L Average Reynolds #: 100500 Number of angles of attack: 49 alpha / Cl / Cm -5.96 -0.387 -0.0312 -4.53 -0.229 -0.0496 -3.52 -0.136 -0.0530 -2.77 -0.068 -0.0542 -1.74 0.025 -0.0570 -0.70 0.143 -0.0591 0.36 0.306 -0.0718 1.41 0.449 -0.0812 2.46 0.590 -0.0864 3.53 0.707 -0.0858 4.61 0.809 -0.0804 5.66 0.895 -0.0746 6.71 0.975 -0.0708 7.75 1.060 -0.0690 8.74 1.117 -0.0635 9.79 1.165 -0.0578 10.78 1.207 -0.0520 11.77 1.232 -0.0475 12.69 1.178 -0.0693 13.58 1.038 -0.1265 14.61 1.024 -0.1348 15.64 1.011 -0.1392 16.68 0.975 -0.1381 17.78 1.027 -0.1458 18.51 1.030 -0.1460 16.86 1.017 -0.1504 15.89 0.980 -0.1443 14.93 0.992 -0.1407 14.05 1.051 -0.1406 12.87 1.166 -0.0898 11.99 1.236 -0.0530 10.89 1.206 -0.0530 10.02 1.171 -0.0576 8.89 1.117 -0.0633 7.99 1.072 -0.0676 7.10 1.003 -0.0709 5.93 0.911 -0.0731 4.98 0.840 -0.0789 3.77 0.734 -0.0860 2.82 0.633 -0.0917 1.91 0.513 -0.0885 0.73 0.356 -0.0805 -0.12 0.227 -0.0698 -1.31 0.059 -0.0577 -2.16 -0.005 -0.0600 -3.34 -0.115 -0.0544 -4.21 -0.194 -0.0527 -5.41 -0.311 -0.0497 -6.38 -0.424 -0.0258 Tabulated from data in file CL01319.DAT & reduced using program Q06.01L Average Reynolds #: 200800 Number of angles of attack: 49 alpha / Cl / Cm -5.85 -0.340 -0.0495 -4.72 -0.180 -0.0677 -3.62 -0.057 -0.0737 -2.46 0.067 -0.0792 -1.67 0.162 -0.0848 -0.49 0.285 -0.0850 0.62 0.415 -0.0863 1.46 0.501 -0.0846 2.62 0.624 -0.0842 3.60 0.738 -0.0828 4.72 0.840 -0.0802 5.51 0.908 -0.0783 6.63 1.001 -0.0752 7.69 1.080 -0.0714 8.72 1.139 -0.0657 9.75 1.189 -0.0591 10.82 1.227 -0.0531 11.82 1.243 -0.0480 12.50 1.241 -0.0466 13.59 1.141 -0.1454 14.74 1.114 -0.1579 15.50 1.020 -0.1598 16.65 1.002 -0.1585 17.81 1.026 -0.1643 18.60 1.039 -0.1649 16.65 0.995 -0.1601 15.78 1.006 -0.1616 15.01 1.022 -0.1570 13.91 1.082 -0.1523 12.86 1.160 -0.1214 11.97 1.240 -0.0506 11.08 1.229 -0.0542 9.89 1.190 -0.0608 9.03 1.151 -0.0656 8.11 1.105 -0.0707 6.83 1.020 -0.0767 5.82 0.942 -0.0797 4.78 0.853 -0.0826 3.74 0.755 -0.0847 2.84 0.650 -0.0866 1.77 0.534 -0.0874 0.71 0.425 -0.0889 -0.30 0.313 -0.0883 -1.32 0.207 -0.0901 -2.37 0.077 -0.0826 -3.37 -0.025 -0.0783 -4.37 -0.137 -0.0728 -5.36 -0.259 -0.0654 -6.41 -0.422 -0.0289 Tabulated from data in file CL01321.DAT & reduced using program Q06.01L Average Reynolds #: 301500 Number of angles of attack: 49 alpha / Cl / Cm -5.88 -0.250 -0.0788 -4.68 -0.112 -0.0869 -3.72 -0.016 -0.0885 -2.70 0.088 -0.0909 -1.61 0.196 -0.0928 -0.57 0.291 -0.0882 0.38 0.416 -0.0881 1.51 0.539 -0.0882 2.61 0.655 -0.0873 3.77 0.767 -0.0862 4.63 0.848 -0.0847 5.54 0.928 -0.0821 6.86 1.036 -0.0783 7.71 1.099 -0.0747 8.54 1.150 -0.0702 9.72 1.208 -0.0625 10.82 1.245 -0.0549 11.56 1.258 -0.0497 12.88 1.254 -0.0550 13.52 1.187 -0.1365 14.62 1.144 -0.1546 15.60 1.038 -0.1605 16.63 1.038 -0.1649 17.47 1.046 -0.1649 18.75 1.054 -0.1695 16.77 1.036 -0.1647 15.78 1.043 -0.1629 15.13 1.115 -0.1616 13.92 1.205 -0.1422 13.07 1.209 -0.1128 12.07 1.260 -0.0485 10.89 1.248 -0.0534 10.01 1.220 -0.0587 9.11 1.182 -0.0643 8.07 1.120 -0.0698 7.07 1.051 -0.0738 5.94 0.960 -0.0773 4.77 0.858 -0.0806 3.93 0.781 -0.0823 2.62 0.652 -0.0845 1.74 0.562 -0.0859 0.87 0.469 -0.0860 -0.30 0.335 -0.0859 -1.33 0.223 -0.0915 -2.47 0.107 -0.0911 -3.21 0.035 -0.0889 -4.33 -0.079 -0.0875 -5.36 -0.187 -0.0841 -6.37 -0.323 -0.0646 Tabulated from data in file CL01323.DAT & reduced using program Q06.01L File S7075A0.LFT created on 10-24-1997 at 19:34:41 using program FORMAT :::::::::::::: S7075A0T.LFT :::::::::::::: Airfoil: S7075 (A) Builder: J. Robertson Comment: flap = 0 degs: Zig-Zag trip type "E" @ x/c = 58.3% (h = 0.017") Number of Reynolds #'s: 4 Average Reynolds #: 60700 Number of angles of attack: 49 alpha / Cl / Cm -5.84 -0.446 -0.0329 -4.57 -0.310 -0.0508 -3.66 -0.221 -0.0543 -2.76 -0.142 -0.0548 -1.47 -0.020 -0.0562 -0.58 0.070 -0.0577 0.31 0.175 -0.0570 1.60 0.327 -0.0669 2.51 0.439 -0.0728 3.45 0.570 -0.0842 4.80 0.746 -0.0896 5.72 0.843 -0.0854 6.63 0.910 -0.0758 7.55 0.977 -0.0672 8.83 1.069 -0.0614 9.71 1.106 -0.0562 10.58 1.144 -0.0490 11.82 1.172 -0.0456 12.65 1.051 -0.0807 13.89 0.976 -0.1123 14.80 0.983 -0.1355 15.70 0.949 -0.1410 16.62 0.963 -0.1424 17.53 1.026 -0.1563 18.87 1.042 -0.1615 16.82 0.989 -0.1477 15.96 0.952 -0.1419 14.78 0.953 -0.1358 13.99 0.956 -0.1343 12.94 1.173 -0.0713 11.83 1.168 -0.0506 11.04 1.161 -0.0506 9.93 1.114 -0.0558 8.83 1.067 -0.0612 8.04 1.017 -0.0669 6.87 0.936 -0.0748 5.69 0.839 -0.0829 4.85 0.765 -0.0909 3.63 0.601 -0.0913 2.78 0.490 -0.0835 1.62 0.352 -0.0741 0.80 0.257 -0.0685 -0.35 0.124 -0.0607 -1.47 0.009 -0.0593 -2.28 -0.066 -0.0614 -3.43 -0.184 -0.0596 -4.59 -0.300 -0.0602 -5.42 -0.389 -0.0572 -6.63 -0.497 -0.0337 Tabulated from data in file CL01805.DAT & reduced using program Q06.01L Average Reynolds #: 100600 Number of angles of attack: 49 alpha / Cl / Cm -5.91 -0.400 -0.0242 -4.60 -0.282 -0.0546 -3.69 -0.197 -0.0601 -2.76 -0.093 -0.0637 -1.42 0.076 -0.0693 -0.49 0.201 -0.0703 0.42 0.310 -0.0740 1.71 0.447 -0.0806 2.62 0.569 -0.0869 3.54 0.672 -0.0873 4.49 0.766 -0.0835 5.83 0.870 -0.0756 6.77 0.942 -0.0705 7.72 1.018 -0.0687 8.61 1.076 -0.0634 9.91 1.129 -0.0547 10.77 1.161 -0.0479 11.63 1.195 -0.0438 12.91 1.199 -0.0484 13.76 1.098 -0.1254 14.61 1.002 -0.1429 15.93 0.996 -0.1503 16.50 0.993 -0.1506 17.88 1.032 -0.1580 18.83 1.010 -0.1552 16.75 0.998 -0.1574 15.90 0.989 -0.1551 15.06 1.008 -0.1511 13.83 1.055 -0.1366 13.07 1.171 -0.0886 12.01 1.203 -0.0466 10.91 1.169 -0.0508 10.10 1.134 -0.0555 8.95 1.084 -0.0633 7.77 1.019 -0.0714 6.95 0.950 -0.0733 5.72 0.854 -0.0777 4.88 0.794 -0.0854 3.68 0.684 -0.0935 2.81 0.582 -0.0961 1.60 0.426 -0.0885 0.78 0.343 -0.0846 -0.39 0.203 -0.0780 -1.24 0.089 -0.0737 -2.41 -0.051 -0.0660 -3.26 -0.160 -0.0629 -4.44 -0.268 -0.0587 -5.62 -0.378 -0.0416 -6.45 -0.433 -0.0176 Tabulated from data in file CL01807.DAT & reduced using program Q06.01L Average Reynolds #: 201000 Number of angles of attack: 49 alpha / Cl / Cm -5.71 -0.293 -0.0683 -4.76 -0.168 -0.0823 -3.32 -0.022 -0.0863 -2.73 0.034 -0.0856 -1.29 0.174 -0.0861 -0.67 0.229 -0.0814 0.76 0.386 -0.0827 1.36 0.455 -0.0847 2.80 0.599 -0.0845 3.78 0.700 -0.0822 4.77 0.796 -0.0802 5.74 0.880 -0.0767 6.72 0.963 -0.0737 7.66 1.038 -0.0707 8.56 1.100 -0.0663 9.84 1.166 -0.0587 10.75 1.204 -0.0524 11.62 1.230 -0.0474 12.89 1.237 -0.0429 13.58 1.168 -0.1173 14.83 1.087 -0.1483 15.74 1.026 -0.1556 16.79 1.008 -0.1530 17.83 1.032 -0.1579 18.78 1.030 -0.1596 16.79 1.033 -0.1585 15.80 1.028 -0.1558 14.82 1.044 -0.1457 13.92 1.123 -0.1365 12.83 1.238 -0.0436 12.07 1.235 -0.0462 10.89 1.208 -0.0528 10.06 1.174 -0.0580 8.88 1.115 -0.0652 8.06 1.067 -0.0696 6.77 0.965 -0.0740 5.84 0.888 -0.0773 4.91 0.806 -0.0805 3.60 0.683 -0.0839 2.65 0.585 -0.0862 1.72 0.489 -0.0866 0.80 0.391 -0.0851 -0.54 0.242 -0.0835 -1.48 0.156 -0.0872 -2.43 0.065 -0.0861 -3.35 -0.023 -0.0854 -4.29 -0.120 -0.0851 -5.66 -0.284 -0.0717 -6.51 -0.410 -0.0295 Tabulated from data in file CL01809.DAT & reduced using program Q06.01L Average Reynolds #: 301400 Number of angles of attack: 49 alpha / Cl / Cm -5.85 -0.305 -0.0671 -4.57 -0.163 -0.0769 -3.67 -0.075 -0.0775 -2.33 0.060 -0.0792 -1.37 0.157 -0.0810 -0.40 0.250 -0.0785 0.55 0.364 -0.0804 1.50 0.468 -0.0808 2.52 0.576 -0.0807 3.57 0.684 -0.0797 4.71 0.797 -0.0781 5.83 0.895 -0.0753 6.92 0.987 -0.0720 7.96 1.070 -0.0681 8.97 1.136 -0.0632 9.94 1.190 -0.0587 10.89 1.227 -0.0526 11.82 1.251 -0.0472 12.72 1.258 -0.0431 13.40 1.229 -0.0809 14.71 1.151 -0.1440 15.74 1.066 -0.1594 16.86 1.048 -0.1605 17.60 1.032 -0.1592 18.71 1.047 -0.1644 16.58 1.051 -0.1621 15.75 1.041 -0.1580 14.96 1.128 -0.1481 13.84 1.199 -0.1154 13.36 1.251 -0.0465 11.80 1.251 -0.0490 10.98 1.229 -0.0538 9.73 1.178 -0.0618 8.88 1.127 -0.0652 7.99 1.069 -0.0694 6.59 0.955 -0.0740 6.05 0.909 -0.0756 4.51 0.775 -0.0799 3.95 0.718 -0.0799 2.80 0.603 -0.0812 1.70 0.488 -0.0813 0.65 0.375 -0.0811 -0.31 0.259 -0.0791 -1.29 0.164 -0.0819 -2.24 0.065 -0.0802 -3.25 -0.035 -0.0790 -4.69 -0.177 -0.0775 -5.25 -0.232 -0.0776 -6.56 -0.394 -0.0412 Tabulated from data in file CL01811.DAT & reduced using program Q06.01L File S7075A0T.LFT created on 10-24-1997 at 19:34:41 using program FORMAT :::::::::::::: S7075B0.LFT :::::::::::::: Airfoil: S7075 (B) Builder: J. Thomas Comment: flap = 0 degs Number of Reynolds #'s: 4 Average Reynolds #: 60500 Number of angles of attack: 49 alpha / Cl / Cm -6.13 -0.380 -0.0470 -4.91 -0.275 -0.0491 -3.97 -0.224 -0.0491 -3.03 -0.150 -0.0473 -1.78 -0.044 -0.0487 -0.84 0.051 -0.0480 0.13 0.174 -0.0526 1.11 0.338 -0.0636 2.45 0.556 -0.0820 3.43 0.673 -0.0751 4.44 0.769 -0.0742 5.45 0.855 -0.0662 6.46 0.926 -0.0616 7.46 1.019 -0.0599 8.45 1.092 -0.0560 9.40 1.147 -0.0541 10.34 1.190 -0.0519 11.55 1.215 -0.0451 12.45 1.036 -0.1044 13.39 1.004 -0.1244 14.38 0.988 -0.1341 15.39 0.994 -0.1408 16.41 1.003 -0.1428 17.43 1.055 -0.1562 18.44 1.046 -0.1618 16.69 1.001 -0.1492 15.83 0.985 -0.1450 14.92 0.956 -0.1393 13.73 0.946 -0.1332 12.92 1.047 -0.1219 11.83 1.162 -0.0574 11.03 1.160 -0.0468 9.96 1.151 -0.0502 8.89 1.104 -0.0548 7.79 1.036 -0.0605 6.95 0.984 -0.0646 5.80 0.887 -0.0669 4.67 0.792 -0.0698 3.81 0.718 -0.0756 2.61 0.583 -0.0849 1.75 0.447 -0.0788 0.62 0.265 -0.0618 -0.47 0.140 -0.0542 -1.27 0.048 -0.0521 -2.36 -0.052 -0.0513 -3.42 -0.152 -0.0513 -4.49 -0.244 -0.0502 -5.57 -0.325 -0.0534 -6.41 -0.398 -0.0460 Tabulated from data in file CL01111.DAT & reduced using program Q06.01L Average Reynolds #: 100600 Number of angles of attack: 49 alpha / Cl / Cm -6.16 -0.359 -0.0393 -4.93 -0.254 -0.0508 -3.96 -0.179 -0.0525 -2.98 -0.084 -0.0553 -1.70 0.079 -0.0659 -0.73 0.209 -0.0712 0.25 0.354 -0.0810 1.25 0.484 -0.0870 2.27 0.589 -0.0848 3.29 0.684 -0.0789 4.34 0.775 -0.0739 5.37 0.868 -0.0690 6.40 0.957 -0.0657 7.39 1.033 -0.0622 8.35 1.088 -0.0573 9.59 1.163 -0.0517 10.55 1.196 -0.0478 11.50 1.214 -0.0429 12.41 1.123 -0.0757 13.31 1.033 -0.1295 14.65 1.024 -0.1500 15.32 1.023 -0.1511 16.34 1.027 -0.1526 17.36 1.021 -0.1554 18.38 1.014 -0.1560 16.88 0.997 -0.1526 15.64 1.021 -0.1571 14.75 1.001 -0.1501 13.86 1.018 -0.1463 12.98 1.061 -0.1307 11.90 1.207 -0.0467 10.83 1.200 -0.0468 9.77 1.166 -0.0520 8.99 1.126 -0.0552 7.90 1.054 -0.0577 6.77 0.990 -0.0634 5.65 0.890 -0.0650 4.84 0.817 -0.0681 3.68 0.713 -0.0736 2.80 0.636 -0.0801 1.61 0.513 -0.0839 0.75 0.411 -0.0811 -0.40 0.253 -0.0695 -1.53 0.094 -0.0614 -2.33 -0.006 -0.0573 -3.45 -0.135 -0.0504 -4.55 -0.228 -0.0490 -5.38 -0.287 -0.0494 -6.53 -0.392 -0.0257 Tabulated from data in file CL01110.DAT & reduced using program Q06.01L Average Reynolds #: 200800 Number of angles of attack: 49 alpha / Cl / Cm -6.22 -0.398 -0.0387 -4.77 -0.184 -0.0661 -3.94 -0.088 -0.0719 -2.86 0.055 -0.0803 -2.00 0.152 -0.0833 -0.94 0.244 -0.0779 0.12 0.348 -0.0757 1.17 0.462 -0.0757 2.24 0.573 -0.0740 3.29 0.680 -0.0724 4.35 0.781 -0.0701 5.38 0.878 -0.0678 6.21 0.952 -0.0656 7.39 1.042 -0.0615 8.36 1.113 -0.0580 9.47 1.186 -0.0542 10.38 1.222 -0.0494 11.29 1.232 -0.0443 12.48 1.221 -0.0454 13.20 1.184 -0.1130 14.31 1.092 -0.1496 15.42 1.046 -0.1505 16.36 1.046 -0.1559 17.32 1.020 -0.1581 18.30 1.025 -0.1610 16.84 1.020 -0.1573 15.78 1.059 -0.1567 14.72 1.137 -0.1523 13.96 1.137 -0.1320 13.04 1.195 -0.1075 12.03 1.228 -0.0416 11.06 1.230 -0.0428 10.08 1.214 -0.0493 8.93 1.150 -0.0535 8.05 1.090 -0.0568 6.94 1.009 -0.0607 5.97 0.930 -0.0642 4.95 0.840 -0.0671 3.89 0.742 -0.0699 2.96 0.651 -0.0728 1.73 0.522 -0.0744 0.82 0.426 -0.0754 -0.26 0.308 -0.0749 -1.19 0.224 -0.0789 -2.30 0.119 -0.0808 -3.26 0.006 -0.0763 -4.37 -0.140 -0.0677 -5.31 -0.257 -0.0608 -6.40 -0.420 -0.0307 Tabulated from data in file CL01113.DAT & reduced using program Q06.01L Average Reynolds #: 301500 Number of angles of attack: 49 alpha / Cl / Cm -6.24 -0.350 -0.0575 -4.94 -0.170 -0.0762 -4.00 -0.065 -0.0799 -2.86 0.052 -0.0802 -1.89 0.148 -0.0792 -0.89 0.252 -0.0780 0.19 0.361 -0.0740 1.10 0.461 -0.0738 2.28 0.589 -0.0743 3.26 0.693 -0.0734 4.27 0.791 -0.0725 5.36 0.893 -0.0710 6.44 0.986 -0.0687 7.46 1.068 -0.0661 8.46 1.147 -0.0633 9.43 1.213 -0.0597 10.61 1.257 -0.0525 11.47 1.263 -0.0480 12.55 1.257 -0.0517 13.38 1.238 -0.0606 14.06 1.221 -0.1366 15.18 1.187 -0.1550 16.32 1.148 -0.1601 17.16 1.076 -0.1618 18.18 1.077 -0.1654 16.88 1.077 -0.1602 16.03 1.164 -0.1605 14.97 1.189 -0.1505 13.89 1.240 -0.1299 13.06 1.262 -0.0551 12.04 1.278 -0.0446 11.03 1.278 -0.0439 9.98 1.257 -0.0510 9.00 1.201 -0.0554 7.98 1.123 -0.0587 6.88 1.038 -0.0620 5.90 0.956 -0.0646 4.86 0.866 -0.0662 3.76 0.754 -0.0679 2.83 0.661 -0.0690 1.65 0.524 -0.0703 0.65 0.411 -0.0710 -0.32 0.306 -0.0714 -1.47 0.196 -0.0770 -2.37 0.101 -0.0771 -3.47 -0.010 -0.0787 -4.54 -0.132 -0.0760 -5.38 -0.230 -0.0724 -6.39 -0.377 -0.0499 Tabulated from data in file CL01115.DAT & reduced using program Q06.01L File S7075B0.LFT created on 10-24-1997 at 19:34:41 using program FORMAT :::::::::::::: S8036.LFT :::::::::::::: Airfoil: S8036 Builder: T. Lampe Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 101200 Number of angles of attack: 49 alpha / Cl / Cm -5.59 -0.384 -0.0337 -4.53 -0.252 -0.0383 -3.47 -0.154 -0.0335 -2.19 -0.059 -0.0264 -1.28 0.009 -0.0213 -0.58 0.077 -0.0212 0.44 0.190 -0.0248 1.51 0.346 -0.0369 2.61 0.500 -0.0490 3.72 0.571 -0.0457 5.09 0.678 -0.0383 5.48 0.714 -0.0372 6.57 0.817 -0.0336 7.65 0.908 -0.0302 8.71 0.990 -0.0272 9.73 1.060 -0.0234 10.75 1.100 -0.0165 11.79 1.129 -0.0099 12.80 1.154 -0.0057 13.82 1.166 -0.0029 14.68 0.717 -0.0755 15.76 0.720 -0.0785 16.81 0.720 -0.0828 17.53 0.714 -0.0825 18.61 0.768 -0.0925 16.64 0.727 -0.0895 16.01 0.730 -0.0894 15.06 0.733 -0.0845 13.72 0.788 -0.0784 13.22 1.165 -0.0133 12.09 1.142 -0.0130 11.20 1.116 -0.0173 10.03 1.079 -0.0250 9.16 1.030 -0.0296 7.97 0.941 -0.0327 7.04 0.865 -0.0359 6.09 0.780 -0.0388 5.11 0.690 -0.0430 3.65 0.573 -0.0488 3.00 0.534 -0.0521 1.96 0.416 -0.0453 0.92 0.253 -0.0323 -0.06 0.127 -0.0259 -1.27 0.016 -0.0246 -2.20 -0.057 -0.0290 -3.13 -0.125 -0.0348 -4.34 -0.229 -0.0406 -5.32 -0.339 -0.0382 -6.32 -0.459 -0.0284 Tabulated from data in file CL01028.DAT & reduced using program Q06.01L Average Reynolds #: 201900 Number of angles of attack: 49 alpha / Cl / Cm -5.57 -0.333 -0.0394 -4.59 -0.260 -0.0358 -3.61 -0.174 -0.0333 -2.60 -0.084 -0.0306 -1.62 0.001 -0.0286 -0.64 0.089 -0.0269 0.44 0.188 -0.0259 1.43 0.291 -0.0241 2.41 0.393 -0.0239 3.74 0.608 -0.0361 4.88 0.741 -0.0407 5.57 0.797 -0.0388 6.55 0.875 -0.0353 8.00 0.980 -0.0284 8.61 1.023 -0.0257 9.99 1.114 -0.0194 10.58 1.139 -0.0156 11.80 1.178 -0.0085 12.66 1.192 -0.0065 13.82 1.212 -0.0046 14.69 1.226 -0.0044 15.96 1.242 -0.0050 16.95 1.251 -0.0083 17.95 1.258 -0.0137 18.55 0.824 -0.0989 16.99 0.779 -0.0929 15.54 0.744 -0.0849 15.11 0.774 -0.0858 14.15 1.218 -0.0059 13.12 1.203 -0.0078 12.12 1.187 -0.0082 11.10 1.160 -0.0132 10.05 1.117 -0.0197 9.21 1.065 -0.0234 8.16 0.993 -0.0279 7.06 0.916 -0.0332 5.83 0.819 -0.0379 4.83 0.738 -0.0413 3.82 0.628 -0.0383 2.77 0.442 -0.0247 1.88 0.337 -0.0223 0.97 0.244 -0.0230 -0.19 0.127 -0.0252 -1.18 0.032 -0.0252 -2.48 -0.082 -0.0282 -3.13 -0.132 -0.0299 -4.30 -0.234 -0.0326 -5.29 -0.306 -0.0369 -6.29 -0.385 -0.0397 Tabulated from data in file CL01030.DAT & reduced using program Q06.01L Average Reynolds #: 302600 Number of angles of attack: 53 alpha / Cl / Cm -5.75 -0.364 -0.0367 -4.81 -0.288 -0.0346 -3.54 -0.177 -0.0316 -2.53 -0.085 -0.0301 -1.41 0.021 -0.0285 -0.58 0.096 -0.0285 0.47 0.209 -0.0288 1.63 0.360 -0.0280 2.66 0.472 -0.0278 3.70 0.587 -0.0288 4.66 0.724 -0.0372 5.67 0.829 -0.0390 6.72 0.904 -0.0337 7.70 0.966 -0.0283 8.64 1.033 -0.0244 9.55 1.098 -0.0207 10.72 1.159 -0.0142 11.93 1.199 -0.0085 12.76 1.216 -0.0071 13.84 1.239 -0.0068 14.64 1.250 -0.0074 15.77 1.273 -0.0086 16.61 1.291 -0.0109 17.74 1.270 -0.0161 18.86 1.260 -0.0259 19.73 1.248 -0.0353 20.61 0.922 -0.1133 18.93 0.871 -0.1021 18.04 0.869 -0.0977 16.64 0.866 -0.0933 15.55 0.943 -0.0881 14.94 0.950 -0.0787 14.38 1.247 -0.0082 13.15 1.222 -0.0062 12.09 1.204 -0.0072 11.22 1.181 -0.0105 10.13 1.132 -0.0160 9.19 1.074 -0.0205 7.98 0.986 -0.0256 6.95 0.915 -0.0306 6.11 0.851 -0.0338 4.97 0.746 -0.0352 3.76 0.596 -0.0293 2.84 0.488 -0.0275 1.92 0.399 -0.0282 0.59 0.254 -0.0287 -0.22 0.135 -0.0288 -1.27 0.032 -0.0285 -2.32 -0.065 -0.0297 -3.43 -0.170 -0.0307 -4.79 -0.289 -0.0340 -5.19 -0.321 -0.0350 -6.81 -0.455 -0.0385 Tabulated from data in file CL01032.DAT & reduced using program Q06.01L Average Reynolds #: 403600 Number of angles of attack: 57 alpha / Cl / Cm -5.92 -0.392 -0.0354 -4.84 -0.297 -0.0348 -3.56 -0.181 -0.0316 -2.79 -0.111 -0.0301 -1.66 -0.002 -0.0296 -0.66 0.089 -0.0292 0.88 0.292 -0.0298 1.57 0.369 -0.0302 2.58 0.478 -0.0302 3.64 0.589 -0.0302 4.68 0.720 -0.0328 5.72 0.833 -0.0364 6.76 0.911 -0.0312 7.77 0.977 -0.0260 8.70 1.048 -0.0225 9.60 1.110 -0.0184 10.75 1.169 -0.0123 11.77 1.204 -0.0087 12.74 1.229 -0.0087 13.72 1.246 -0.0096 14.74 1.267 -0.0096 15.77 1.280 -0.0121 16.80 1.280 -0.0192 17.92 1.273 -0.0266 18.76 1.267 -0.0353 20.09 1.265 -0.0507 20.63 1.251 -0.0631 21.55 1.231 -0.0929 22.48 1.119 -0.1018 20.90 1.245 -0.0715 20.19 1.258 -0.0535 19.07 1.265 -0.0394 18.05 1.265 -0.0292 17.09 1.273 -0.0230 16.18 1.272 -0.0139 15.18 1.270 -0.0119 14.25 1.258 -0.0107 13.23 1.241 -0.0091 12.22 1.218 -0.0074 11.23 1.187 -0.0080 10.22 1.143 -0.0127 9.13 1.078 -0.0179 8.08 1.001 -0.0226 7.10 0.931 -0.0270 6.04 0.864 -0.0332 4.94 0.746 -0.0324 3.77 0.605 -0.0286 2.86 0.510 -0.0287 1.95 0.412 -0.0293 0.69 0.274 -0.0294 -0.37 0.155 -0.0295 -1.77 -0.007 -0.0294 -2.17 -0.045 -0.0296 -3.67 -0.194 -0.0315 -4.31 -0.249 -0.0328 -5.23 -0.328 -0.0342 -6.41 -0.437 -0.0355 Tabulated from data in file CL01036.DAT & reduced using program Q06.01L Average Reynolds #: 504800 Number of angles of attack: 53 alpha / Cl / Cm -6.67 -0.490 -0.0364 -4.34 -0.279 -0.0335 -3.32 -0.191 -0.0314 -2.70 -0.136 -0.0300 -1.57 -0.023 -0.0297 -0.50 0.098 -0.0297 0.69 0.231 -0.0303 1.89 0.366 -0.0311 2.59 0.442 -0.0311 4.03 0.591 -0.0311 4.84 0.677 -0.0311 5.68 0.773 -0.0327 7.23 0.904 -0.0290 8.05 0.967 -0.0259 8.81 1.025 -0.0229 10.07 1.110 -0.0170 10.76 1.145 -0.0133 11.93 1.186 -0.0086 13.01 1.216 -0.0092 14.07 1.239 -0.0109 15.12 1.251 -0.0136 15.68 1.261 -0.0159 17.14 1.279 -0.0350 17.71 1.289 -0.0397 19.07 1.269 -0.0413 20.04 1.267 -0.0567 20.68 1.260 -0.0710 18.77 1.271 -0.0389 17.88 1.267 -0.0297 16.90 1.276 -0.0326 16.11 1.263 -0.0196 14.90 1.253 -0.0142 14.05 1.241 -0.0125 12.89 1.215 -0.0100 12.06 1.192 -0.0080 10.78 1.147 -0.0116 9.79 1.095 -0.0170 8.70 1.017 -0.0220 7.61 0.931 -0.0264 6.91 0.880 -0.0297 5.66 0.767 -0.0314 4.98 0.691 -0.0302 3.60 0.545 -0.0306 2.76 0.457 -0.0309 1.26 0.296 -0.0309 0.47 0.208 -0.0304 -0.32 0.119 -0.0300 -1.56 -0.021 -0.0300 -2.78 -0.146 -0.0307 -3.47 -0.208 -0.0321 -4.72 -0.317 -0.0342 -5.33 -0.373 -0.0347 -6.57 -0.482 -0.0360 Tabulated from data in file CL01770.DAT & reduced using program Q06.01L File S8036.LFT created on 10-24-1997 at 19:34:41 using program FORMAT :::::::::::::: S8037.LFT :::::::::::::: Airfoil: S8037 Builder: T. Lampe Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 101100 Number of angles of attack: 57 alpha / Cl / Cm -6.42 -0.326 -0.0562 -4.88 -0.223 -0.0570 -3.95 -0.178 -0.0501 -2.74 -0.101 -0.0383 -1.83 -0.041 -0.0296 -0.39 0.127 -0.0330 0.28 0.236 -0.0415 1.21 0.392 -0.0544 2.42 0.499 -0.0570 3.35 0.560 -0.0502 4.31 0.643 -0.0458 5.79 0.780 -0.0425 6.47 0.838 -0.0410 7.39 0.918 -0.0388 8.82 1.039 -0.0346 9.46 1.092 -0.0333 10.86 1.184 -0.0274 11.50 1.212 -0.0238 12.38 1.237 -0.0171 13.54 1.250 -0.0106 14.43 1.252 -0.0075 15.83 1.252 -0.0057 16.46 1.246 -0.0075 17.71 0.812 -0.0866 18.35 0.796 -0.0829 19.28 0.819 -0.0876 20.48 0.886 -0.1030 21.36 0.887 -0.1046 22.84 0.943 -0.1168 20.82 0.872 -0.1127 19.80 0.839 -0.1031 18.76 0.812 -0.0963 17.70 0.771 -0.0902 16.55 0.747 -0.0826 15.75 0.752 -0.0800 14.72 0.795 -0.0811 13.74 0.909 -0.0747 12.78 1.243 -0.0244 11.78 1.229 -0.0288 10.76 1.186 -0.0341 9.76 1.123 -0.0377 8.74 1.039 -0.0395 7.71 0.951 -0.0424 6.95 0.884 -0.0443 5.64 0.769 -0.0469 4.84 0.697 -0.0486 3.83 0.607 -0.0525 2.81 0.533 -0.0578 1.79 0.470 -0.0641 0.77 0.327 -0.0536 -0.25 0.157 -0.0407 -1.57 -0.007 -0.0355 -2.28 -0.055 -0.0406 -3.56 -0.147 -0.0513 -4.31 -0.193 -0.0588 -5.66 -0.268 -0.0638 -6.47 -0.327 -0.0612 Tabulated from data in file CL01039.DAT & reduced using program Q06.01L Average Reynolds #: 201800 Number of angles of attack: 57 alpha / Cl / Cm -6.04 -0.320 -0.0494 -4.80 -0.226 -0.0474 -3.89 -0.166 -0.0436 -2.40 -0.044 -0.0378 -1.76 0.012 -0.0356 -0.87 0.090 -0.0330 0.31 0.204 -0.0308 1.20 0.302 -0.0315 2.39 0.474 -0.0418 3.60 0.638 -0.0521 4.26 0.693 -0.0502 5.46 0.796 -0.0466 6.36 0.878 -0.0444 7.52 0.979 -0.0406 8.39 1.050 -0.0378 9.51 1.134 -0.0331 10.35 1.186 -0.0289 11.45 1.245 -0.0224 12.51 1.270 -0.0139 13.55 1.273 -0.0114 14.61 1.271 -0.0093 15.79 1.273 -0.0080 16.58 1.272 -0.0075 17.76 1.289 -0.0127 18.55 1.290 -0.0170 19.69 1.267 -0.0229 20.46 1.253 -0.0293 21.48 1.246 -0.0402 22.27 0.899 -0.1100 20.40 0.861 -0.1038 19.79 0.861 -0.1051 18.46 0.828 -0.0968 17.89 0.808 -0.0907 16.70 0.807 -0.0851 15.86 0.823 -0.0827 14.73 0.875 -0.0770 13.75 1.278 -0.0130 12.84 1.279 -0.0142 11.99 1.270 -0.0197 10.81 1.216 -0.0272 9.91 1.160 -0.0319 8.99 1.095 -0.0359 7.73 0.994 -0.0406 6.66 0.900 -0.0437 5.88 0.832 -0.0456 4.82 0.739 -0.0485 3.73 0.651 -0.0522 2.51 0.493 -0.0439 1.72 0.369 -0.0339 0.67 0.242 -0.0303 -0.37 0.134 -0.0304 -1.38 0.041 -0.0328 -2.42 -0.046 -0.0360 -3.49 -0.134 -0.0395 -4.56 -0.207 -0.0441 -5.42 -0.268 -0.0478 -6.60 -0.355 -0.0504 Tabulated from data in file CL01041.DAT & reduced using program Q06.01L Average Reynolds #: 302500 Number of angles of attack: 57 alpha / Cl / Cm -6.05 -0.338 -0.0450 -4.79 -0.231 -0.0437 -3.85 -0.157 -0.0411 -2.85 -0.079 -0.0370 -1.79 0.014 -0.0346 -0.70 0.121 -0.0336 0.43 0.236 -0.0324 1.22 0.315 -0.0311 2.29 0.438 -0.0325 3.34 0.586 -0.0414 4.43 0.734 -0.0496 5.56 0.835 -0.0472 6.32 0.899 -0.0447 7.40 0.985 -0.0405 8.45 1.062 -0.0356 9.47 1.133 -0.0303 10.45 1.194 -0.0250 11.42 1.243 -0.0192 12.77 1.266 -0.0114 13.78 1.279 -0.0135 14.42 1.284 -0.0132 15.81 1.280 -0.0102 16.46 1.284 -0.0121 17.85 1.295 -0.0138 18.47 1.298 -0.0175 19.88 1.289 -0.0267 20.53 1.278 -0.0315 22.07 1.298 -0.0474 22.45 1.288 -0.0507 20.92 1.278 -0.0362 19.90 1.286 -0.0286 18.88 1.299 -0.0215 17.90 1.301 -0.0165 16.94 1.301 -0.0136 15.98 1.292 -0.0133 15.01 1.290 -0.0144 14.03 1.283 -0.0150 13.08 1.273 -0.0133 11.89 1.257 -0.0159 11.08 1.226 -0.0212 10.01 1.163 -0.0271 8.89 1.089 -0.0328 7.95 1.022 -0.0374 6.93 0.944 -0.0419 5.85 0.855 -0.0460 4.70 0.758 -0.0496 3.82 0.653 -0.0467 2.67 0.485 -0.0367 1.43 0.336 -0.0326 0.54 0.243 -0.0339 -0.38 0.149 -0.0348 -1.31 0.056 -0.0353 -2.58 -0.058 -0.0376 -3.56 -0.138 -0.0406 -4.52 -0.208 -0.0438 -5.47 -0.290 -0.0454 -6.42 -0.369 -0.0473 Tabulated from data in file CL01043.DAT & reduced using program Q06.01L Average Reynolds #: 403400 Number of angles of attack: 57 alpha / Cl / Cm -5.98 -0.340 -0.0437 -4.88 -0.241 -0.0433 -3.84 -0.151 -0.0411 -2.63 -0.057 -0.0364 -1.71 0.025 -0.0347 -0.76 0.121 -0.0340 0.24 0.228 -0.0338 1.26 0.334 -0.0332 2.36 0.452 -0.0334 3.46 0.587 -0.0377 4.56 0.734 -0.0456 5.63 0.849 -0.0479 6.40 0.909 -0.0449 7.55 0.994 -0.0390 8.64 1.072 -0.0336 9.38 1.122 -0.0298 10.88 1.206 -0.0211 11.53 1.231 -0.0164 12.78 1.262 -0.0141 13.71 1.273 -0.0151 14.58 1.281 -0.0153 15.88 1.279 -0.0143 16.49 1.282 -0.0162 17.82 1.275 -0.0199 18.46 1.279 -0.0218 19.65 1.263 -0.0267 20.53 1.252 -0.0328 21.73 1.291 -0.0455 22.40 1.308 -0.0563 21.01 1.279 -0.0377 19.95 1.284 -0.0291 19.01 1.290 -0.0231 17.92 1.284 -0.0194 16.97 1.289 -0.0162 15.98 1.293 -0.0150 14.94 1.288 -0.0157 13.97 1.275 -0.0155 12.96 1.264 -0.0132 12.00 1.240 -0.0111 11.06 1.212 -0.0161 10.03 1.158 -0.0227 8.88 1.083 -0.0294 7.84 1.010 -0.0347 6.61 0.919 -0.0409 5.64 0.846 -0.0452 4.62 0.735 -0.0435 3.64 0.603 -0.0373 2.66 0.478 -0.0330 1.60 0.363 -0.0326 0.44 0.242 -0.0337 -0.35 0.160 -0.0342 -1.38 0.052 -0.0347 -2.42 -0.044 -0.0358 -3.44 -0.125 -0.0391 -4.39 -0.204 -0.0414 -5.63 -0.311 -0.0436 -6.50 -0.385 -0.0446 Tabulated from data in file CL01045.DAT & reduced using program Q06.01L Average Reynolds #: 504500 Number of angles of attack: 53 alpha / Cl / Cm -7.31 -0.479 -0.0468 -4.69 -0.261 -0.0421 -3.76 -0.180 -0.0406 -2.83 -0.104 -0.0381 -1.79 -0.015 -0.0354 -0.72 0.094 -0.0345 0.43 0.219 -0.0344 1.60 0.345 -0.0341 2.32 0.422 -0.0340 3.63 0.565 -0.0350 4.89 0.724 -0.0402 5.62 0.818 -0.0446 7.05 0.942 -0.0410 7.90 1.002 -0.0364 8.72 1.061 -0.0323 10.05 1.149 -0.0250 10.79 1.191 -0.0211 11.98 1.231 -0.0145 12.57 1.242 -0.0127 13.60 1.264 -0.0138 14.66 1.278 -0.0145 15.73 1.286 -0.0149 16.80 1.296 -0.0159 17.80 1.295 -0.0178 18.83 1.304 -0.0236 19.80 1.308 -0.0322 20.88 1.319 -0.0407 18.61 1.310 -0.0260 17.85 1.301 -0.0195 16.66 1.294 -0.0168 15.84 1.295 -0.0162 14.66 1.281 -0.0148 13.87 1.271 -0.0143 12.69 1.246 -0.0112 11.91 1.231 -0.0124 10.57 1.178 -0.0199 9.61 1.119 -0.0244 8.53 1.044 -0.0297 7.86 0.996 -0.0338 6.64 0.908 -0.0407 5.26 0.767 -0.0410 4.51 0.669 -0.0367 3.74 0.572 -0.0336 2.19 0.403 -0.0334 1.41 0.320 -0.0339 0.65 0.238 -0.0344 -0.70 0.094 -0.0344 -1.88 -0.026 -0.0352 -2.53 -0.083 -0.0370 -3.72 -0.183 -0.0403 -4.81 -0.278 -0.0423 -5.87 -0.371 -0.0439 -6.48 -0.422 -0.0450 Tabulated from data in file CL01788.DAT & reduced using program Q06.01L File S8037.LFT created on 10-24-1997 at 19:34:41 using program FORMAT :::::::::::::: S8052.LFT :::::::::::::: Airfoil: S8052 Builder: M. Fox Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 101000 Number of angles of attack: 49 alpha / Cl / Cm -5.89 -0.449 -0.0226 -4.59 -0.378 -0.0196 -3.67 -0.276 -0.0260 -2.75 -0.158 -0.0303 -1.46 -0.045 -0.0274 -0.55 0.056 -0.0271 0.37 0.200 -0.0395 1.60 0.313 -0.0452 2.52 0.377 -0.0408 3.47 0.458 -0.0373 4.43 0.555 -0.0351 5.72 0.687 -0.0342 6.66 0.778 -0.0329 7.65 0.872 -0.0336 8.55 0.953 -0.0329 9.80 1.041 -0.0313 10.69 1.102 -0.0297 11.58 1.150 -0.0286 12.80 1.182 -0.0270 13.69 1.180 -0.0280 14.49 0.826 -0.0955 15.81 0.852 -0.1064 16.76 0.843 -0.1075 17.74 0.893 -0.1131 18.72 0.894 -0.1123 16.92 0.863 -0.1084 16.00 0.841 -0.0959 15.09 0.840 -0.0940 13.91 0.802 -0.0929 13.04 0.867 -0.0936 12.01 1.165 -0.0261 11.17 1.123 -0.0110 10.03 1.054 -0.0122 9.19 0.998 -0.0129 8.07 0.910 -0.0157 6.89 0.796 -0.0147 5.97 0.710 -0.0143 5.01 0.615 -0.0154 3.82 0.493 -0.0195 2.89 0.404 -0.0230 1.91 0.332 -0.0281 0.77 0.259 -0.0342 -0.14 0.116 -0.0251 -1.26 -0.019 -0.0173 -2.15 -0.095 -0.0198 -3.28 -0.203 -0.0232 -4.18 -0.325 -0.0122 -5.32 -0.419 -0.0080 -6.23 -0.463 -0.0119 Tabulated from data in file CL01412.DAT & reduced using program Q06.01L Average Reynolds #: 201600 Number of angles of attack: 49 alpha / Cl / Cm -5.89 -0.449 -0.0254 -4.53 -0.303 -0.0310 -3.54 -0.216 -0.0318 -2.54 -0.132 -0.0283 -1.55 -0.045 -0.0258 -0.51 0.047 -0.0239 0.50 0.130 -0.0174 1.61 0.238 -0.0178 2.65 0.373 -0.0246 3.65 0.480 -0.0253 4.70 0.607 -0.0253 5.66 0.702 -0.0254 6.63 0.799 -0.0262 7.59 0.892 -0.0260 8.81 0.993 -0.0251 9.73 1.061 -0.0247 10.63 1.120 -0.0228 11.80 1.178 -0.0203 12.67 1.205 -0.0195 13.82 1.217 -0.0262 14.71 1.185 -0.0346 15.64 1.142 -0.0471 16.61 1.112 -0.0541 17.67 0.892 -0.1201 18.59 0.910 -0.1239 16.86 0.891 -0.1230 15.83 0.867 -0.1189 14.76 0.842 -0.1163 13.72 0.845 -0.1117 13.03 0.935 -0.1100 12.30 1.194 -0.0253 11.18 1.149 -0.0236 10.09 1.082 -0.0259 8.98 1.000 -0.0275 8.10 0.928 -0.0284 6.96 0.822 -0.0285 6.04 0.737 -0.0281 4.84 0.619 -0.0282 3.84 0.490 -0.0278 2.87 0.389 -0.0266 1.93 0.271 -0.0217 0.70 0.141 -0.0203 -0.37 0.059 -0.0258 -1.35 -0.030 -0.0283 -2.36 -0.118 -0.0313 -3.34 -0.199 -0.0344 -4.33 -0.288 -0.0367 -5.32 -0.386 -0.0349 -6.30 -0.501 -0.0278 Tabulated from data in file CL01415.DAT & reduced using program Q06.01L Average Reynolds #: 302100 Number of angles of attack: 51 alpha / Cl / Cm -5.98 -0.472 -0.0256 -4.62 -0.351 -0.0242 -3.62 -0.256 -0.0241 -2.58 -0.154 -0.0236 -1.38 -0.039 -0.0222 -0.66 0.031 -0.0215 0.55 0.142 -0.0205 1.47 0.256 -0.0183 2.46 0.368 -0.0180 3.48 0.497 -0.0223 4.52 0.607 -0.0238 5.78 0.735 -0.0257 6.50 0.806 -0.0266 7.78 0.930 -0.0275 8.72 1.014 -0.0271 9.65 1.088 -0.0260 10.58 1.154 -0.0242 11.77 1.227 -0.0216 12.64 1.255 -0.0204 13.73 1.240 -0.0409 15.00 1.192 -0.0583 15.67 1.142 -0.0661 16.88 1.096 -0.0677 17.85 1.076 -0.0728 18.18 0.963 -0.1330 19.53 0.945 -0.1381 18.10 0.977 -0.1340 16.78 1.062 -0.1286 16.13 1.088 -0.1255 15.18 1.059 -0.1149 14.28 1.224 -0.0569 13.18 1.254 -0.0351 12.19 1.242 -0.0238 11.12 1.189 -0.0242 10.04 1.117 -0.0260 9.21 1.055 -0.0273 8.10 0.960 -0.0280 6.94 0.849 -0.0281 6.07 0.761 -0.0277 4.84 0.637 -0.0270 3.90 0.538 -0.0263 2.92 0.430 -0.0251 1.94 0.308 -0.0207 0.81 0.170 -0.0228 -0.16 0.067 -0.0240 -1.32 -0.031 -0.0253 -2.40 -0.137 -0.0264 -3.46 -0.240 -0.0272 -4.19 -0.310 -0.0272 -5.74 -0.448 -0.0298 -6.51 -0.517 -0.0303 Tabulated from data in file CL01418.DAT & reduced using program Q06.01L Average Reynolds #: 402900 Number of angles of attack: 50 alpha / Cl / Cm -5.96 -0.494 -0.0232 -4.73 -0.375 -0.0234 -3.78 -0.280 -0.0236 -2.51 -0.149 -0.0240 -1.73 -0.070 -0.0233 -0.42 0.048 -0.0229 0.24 0.144 -0.0230 1.44 0.277 -0.0225 2.62 0.405 -0.0222 3.46 0.498 -0.0233 4.62 0.626 -0.0257 5.76 0.743 -0.0269 6.56 0.826 -0.0277 7.66 0.934 -0.0283 8.71 1.030 -0.0276 9.74 1.116 -0.0266 10.74 1.187 -0.0245 11.72 1.237 -0.0225 12.66 1.259 -0.0265 13.83 1.221 -0.0543 14.83 1.186 -0.0642 15.66 1.137 -0.0763 16.91 1.078 -0.0804 17.79 1.069 -0.0838 18.64 1.060 -0.0890 18.42 0.928 -0.1399 17.11 1.043 -0.1393 16.07 1.131 -0.1285 15.71 1.124 -0.0721 13.96 1.208 -0.0550 12.97 1.246 -0.0428 12.05 1.253 -0.0239 11.20 1.224 -0.0227 10.03 1.150 -0.0249 9.12 1.078 -0.0263 8.17 0.993 -0.0271 6.92 0.874 -0.0270 5.90 0.771 -0.0268 4.85 0.662 -0.0260 3.77 0.547 -0.0249 3.01 0.458 -0.0228 1.92 0.342 -0.0231 0.80 0.218 -0.0241 -0.65 0.025 -0.0236 -1.29 -0.025 -0.0241 -2.53 -0.153 -0.0247 -3.41 -0.243 -0.0243 -4.61 -0.364 -0.0240 -5.48 -0.449 -0.0241 -6.66 -0.551 -0.0255 Tabulated from data in file CL01421.DAT & reduced using program Q06.01L Average Reynolds #: 503900 Number of angles of attack: 49 alpha / Cl / Cm -6.32 -0.559 -0.0246 -4.40 -0.375 -0.0246 -3.37 -0.269 -0.0247 -2.31 -0.160 -0.0251 -1.15 -0.039 -0.0250 -0.45 0.035 -0.0249 0.85 0.179 -0.0245 1.53 0.254 -0.0245 2.97 0.410 -0.0244 3.81 0.497 -0.0237 4.63 0.586 -0.0256 6.01 0.732 -0.0259 6.79 0.811 -0.0271 8.14 0.947 -0.0282 8.88 1.017 -0.0277 10.15 1.125 -0.0266 10.86 1.179 -0.0256 12.08 1.243 -0.0230 12.71 1.260 -0.0240 13.77 1.226 -0.0484 15.16 1.183 -0.0689 15.68 1.157 -0.0704 16.94 1.104 -0.0827 17.82 1.079 -0.0873 18.66 1.072 -0.0918 16.40 1.126 -0.0812 16.22 1.136 -0.0793 14.64 1.209 -0.0615 13.67 1.236 -0.0477 12.91 1.263 -0.0253 11.81 1.231 -0.0181 10.87 1.176 -0.0202 9.87 1.098 -0.0226 8.84 1.009 -0.0244 7.76 0.905 -0.0250 6.63 0.790 -0.0250 6.02 0.727 -0.0244 4.82 0.603 -0.0230 3.53 0.464 -0.0226 2.77 0.385 -0.0239 1.26 0.222 -0.0246 0.47 0.134 -0.0245 -0.26 0.053 -0.0248 -1.65 -0.094 -0.0252 -2.38 -0.173 -0.0251 -3.64 -0.301 -0.0248 -4.33 -0.371 -0.0247 -5.62 -0.499 -0.0248 -6.82 -0.604 -0.0258 Tabulated from data in file CL01768.DAT & reduced using program Q06.01L File S8052.LFT created on 10-24-1997 at 19:34:41 using program FORMAT :::::::::::::: SA7035.LFT :::::::::::::: Airfoil: SA7035 Builder: M. Allen Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 60006 Number of angles of attack: 59 alpha / Cl / Cm -8.97 -0.485 0.0143 -7.81 -0.431 -0.0139 -6.90 -0.392 -0.0486 -5.89 -0.316 -0.0641 -4.97 -0.250 -0.0624 -3.83 -0.173 -0.0572 -2.95 -0.110 -0.0572 -1.87 -0.049 -0.0470 -0.92 0.034 -0.0525 0.17 0.103 -0.0566 1.18 0.246 -0.0559 2.14 0.416 -0.0777 3.21 0.522 -0.0856 4.22 0.620 -0.0832 5.28 0.712 -0.0733 6.28 0.793 -0.0660 7.31 0.879 -0.0595 8.44 0.970 -0.0518 9.49 1.035 -0.0461 10.44 1.089 -0.0424 11.36 1.124 -0.0379 12.46 1.133 -0.0358 13.49 0.913 -0.1216 14.35 0.866 -0.1328 15.32 0.917 -0.1384 16.25 0.923 -0.1443 17.38 0.966 -0.1523 18.34 0.983 -0.1504 19.54 0.984 -0.1599 20.34 1.052 -0.1720 19.65 1.001 -0.1737 18.66 0.961 -0.1681 17.67 0.971 -0.1505 16.71 0.992 -0.1494 15.66 0.928 -0.1495 14.65 0.896 -0.1417 13.66 0.906 -0.1387 12.70 1.029 -0.0439 11.86 1.148 -0.0383 10.83 1.131 -0.0417 9.80 1.078 -0.0452 8.71 1.005 -0.0495 7.74 0.938 -0.0530 6.77 0.861 -0.0621 5.62 0.766 -0.0682 4.69 0.688 -0.0762 3.66 0.587 -0.0865 2.57 0.474 -0.0870 1.58 0.325 -0.0743 0.60 0.194 -0.0531 -0.48 0.097 -0.0472 -1.48 -0.004 -0.0423 -2.47 -0.076 -0.0457 -3.53 -0.149 -0.0478 -4.53 -0.217 -0.0507 -5.64 -0.295 -0.0502 -6.68 -0.368 -0.0445 -7.53 -0.415 -0.0099 -8.58 -0.487 0.0170 Tabulated from data in file ag02583.dat & reduced using program C06.01 Average Reynolds #: 99908 Number of angles of attack: 59 alpha / Cl / Cm -8.91 -0.515 0.0387 -7.97 -0.482 0.0147 -7.00 -0.426 -0.0242 -5.89 -0.333 -0.0542 -4.89 -0.247 -0.0531 -3.91 -0.166 -0.0501 -2.89 -0.078 -0.0513 -1.90 -0.007 -0.0459 -0.83 0.080 -0.0481 0.24 0.236 -0.0642 1.14 0.391 -0.0767 2.28 0.508 -0.0750 3.29 0.593 -0.0681 4.36 0.680 -0.0614 5.35 0.768 -0.0564 6.60 0.871 -0.0521 7.42 0.942 -0.0495 8.44 1.028 -0.0468 9.51 1.101 -0.0421 10.45 1.155 -0.0376 11.57 1.175 -0.0315 12.40 1.176 -0.0291 13.25 0.995 -0.1301 14.37 0.944 -0.1390 15.31 0.947 -0.1466 16.29 0.981 -0.1527 17.34 0.963 -0.1597 18.32 0.977 -0.1541 19.30 0.948 -0.1612 20.39 0.972 -0.1673 19.47 0.987 -0.1828 18.61 1.007 -0.1701 17.56 0.964 -0.1685 16.58 0.958 -0.1630 15.64 0.994 -0.1587 14.63 0.930 -0.1579 13.71 0.953 -0.1513 12.89 1.166 -0.0444 11.77 1.174 -0.0371 10.85 1.158 -0.0409 9.79 1.122 -0.0469 8.82 1.063 -0.0515 7.75 0.981 -0.0548 6.64 0.876 -0.0570 5.65 0.782 -0.0596 4.65 0.693 -0.0640 3.63 0.604 -0.0701 2.64 0.519 -0.0764 1.49 0.417 -0.0836 0.56 0.281 -0.0761 -0.49 0.113 -0.0587 -1.48 -0.008 -0.0495 -2.51 -0.084 -0.0526 -3.52 -0.158 -0.0510 -4.57 -0.228 -0.0529 -5.54 -0.296 -0.0554 -6.56 -0.397 -0.0464 -7.56 -0.482 0.0007 -8.52 -0.533 0.0222 Tabulated from data in file ag02575.dat & reduced using program C06.01 Average Reynolds #: 149946 Number of angles of attack: 59 alpha / Cl / Cm -8.92 -0.506 0.0411 -7.95 -0.473 0.0211 -6.66 -0.398 -0.0302 -5.95 -0.330 -0.0516 -4.86 -0.244 -0.0512 -3.82 -0.164 -0.0494 -2.81 -0.064 -0.0521 -1.86 0.048 -0.0569 -0.63 0.202 -0.0667 0.32 0.328 -0.0725 1.25 0.412 -0.0682 2.19 0.494 -0.0639 3.34 0.611 -0.0605 4.34 0.698 -0.0578 5.27 0.790 -0.0561 6.27 0.881 -0.0532 7.66 1.002 -0.0500 8.43 1.063 -0.0474 9.70 1.134 -0.0415 10.59 1.171 -0.0358 11.58 1.188 -0.0304 12.82 1.172 -0.0306 13.60 1.147 -0.0358 14.14 0.980 -0.1512 15.63 0.993 -0.1540 16.63 0.952 -0.1604 17.50 0.979 -0.1566 18.50 0.968 -0.1613 19.37 0.967 -0.1663 20.37 1.019 -0.1735 19.49 0.996 -0.1715 18.47 0.981 -0.1682 17.39 0.962 -0.1644 16.55 0.970 -0.1636 15.50 0.955 -0.1618 14.55 0.957 -0.1555 13.58 0.970 -0.1475 12.83 1.173 -0.0356 11.84 1.188 -0.0356 10.82 1.181 -0.0402 9.77 1.147 -0.0466 8.83 1.090 -0.0511 7.81 1.020 -0.0545 6.75 0.921 -0.0565 5.66 0.818 -0.0588 4.67 0.730 -0.0610 3.66 0.631 -0.0634 2.64 0.541 -0.0663 1.61 0.440 -0.0694 0.49 0.331 -0.0759 -0.49 0.218 -0.0744 -1.47 0.056 -0.0625 -2.46 -0.061 -0.0554 -3.62 -0.161 -0.0509 -4.74 -0.253 -0.0518 -5.52 -0.312 -0.0550 -6.56 -0.404 -0.0408 -7.52 -0.475 0.0002 -8.64 -0.506 0.0295 Tabulated from data in file ag02577.dat & reduced using program C06.01 Average Reynolds #: 199814 Number of angles of attack: 59 alpha / Cl / Cm -8.95 -0.529 0.0446 -7.88 -0.511 0.0174 -6.90 -0.446 -0.0244 -5.78 -0.330 -0.0538 -4.77 -0.255 -0.0501 -3.68 -0.152 -0.0514 -2.77 -0.045 -0.0583 -1.70 0.102 -0.0698 -0.68 0.220 -0.0715 0.40 0.335 -0.0680 1.24 0.417 -0.0648 2.43 0.528 -0.0620 3.40 0.625 -0.0603 4.33 0.715 -0.0587 5.35 0.821 -0.0569 6.42 0.928 -0.0553 7.37 1.010 -0.0530 8.46 1.096 -0.0498 9.77 1.174 -0.0436 10.40 1.205 -0.0400 11.43 1.212 -0.0328 12.41 1.204 -0.0335 13.38 1.191 -0.0451 14.42 1.172 -0.0583 15.51 0.999 -0.1602 16.57 1.006 -0.1616 17.38 1.017 -0.1598 18.48 0.969 -0.1663 19.40 1.001 -0.1699 20.44 1.034 -0.1838 19.45 1.013 -0.1772 18.43 0.973 -0.1749 17.50 1.031 -0.1720 16.26 1.005 -0.1638 15.44 1.000 -0.1647 14.41 0.984 -0.1594 13.75 1.191 -0.0515 12.85 1.196 -0.0392 11.88 1.206 -0.0334 10.83 1.202 -0.0384 9.85 1.180 -0.0450 8.58 1.100 -0.0510 7.42 1.008 -0.0547 6.73 0.947 -0.0564 5.65 0.843 -0.0586 4.38 0.716 -0.0604 3.65 0.641 -0.0617 2.52 0.527 -0.0633 1.56 0.429 -0.0653 0.59 0.335 -0.0688 -0.58 0.224 -0.0733 -1.57 0.108 -0.0714 -2.74 -0.060 -0.0594 -3.73 -0.179 -0.0517 -4.57 -0.259 -0.0503 -5.62 -0.335 -0.0543 -6.58 -0.425 -0.0431 -7.52 -0.508 -0.0021 -8.84 -0.559 0.0369 Tabulated from data in file ag02579.dat & reduced using program C06.01 Average Reynolds #: 299769 Number of angles of attack: 59 alpha / Cl / Cm -9.03 -0.581 0.0441 -8.03 -0.556 0.0129 -6.88 -0.469 -0.0355 -5.83 -0.365 -0.0564 -4.89 -0.267 -0.0564 -3.91 -0.139 -0.0641 -2.92 -0.007 -0.0737 -1.92 0.105 -0.0750 -0.77 0.202 -0.0672 0.36 0.324 -0.0659 1.76 0.472 -0.0644 2.32 0.528 -0.0634 3.43 0.649 -0.0625 4.46 0.752 -0.0611 5.37 0.844 -0.0596 6.38 0.946 -0.0578 7.46 1.048 -0.0557 8.55 1.138 -0.0522 9.51 1.201 -0.0477 10.57 1.242 -0.0404 11.41 1.252 -0.0346 12.36 1.243 -0.0353 13.58 1.224 -0.0522 14.43 1.193 -0.0643 15.20 1.085 -0.1550 16.07 1.052 -0.1647 17.08 1.007 -0.1659 18.07 1.002 -0.1699 19.12 1.017 -0.1692 20.11 1.043 -0.1891 19.74 1.025 -0.1809 18.69 0.995 -0.1747 17.69 1.007 -0.1725 16.67 1.008 -0.1687 15.75 1.015 -0.1633 14.69 1.106 -0.1610 14.18 1.216 -0.0579 12.76 1.233 -0.0428 11.89 1.235 -0.0372 10.80 1.243 -0.0408 9.86 1.221 -0.0457 8.78 1.153 -0.0505 7.62 1.062 -0.0541 6.62 0.973 -0.0568 5.57 0.871 -0.0593 4.57 0.769 -0.0613 3.51 0.661 -0.0633 2.45 0.546 -0.0646 1.33 0.425 -0.0661 0.23 0.308 -0.0676 -0.61 0.214 -0.0676 -1.62 0.131 -0.0757 -2.69 0.022 -0.0764 -3.61 -0.102 -0.0682 -4.79 -0.260 -0.0581 -5.83 -0.363 -0.0584 -7.04 -0.484 -0.0313 -7.65 -0.537 0.0002 -8.50 -0.572 0.0290 Tabulated from data in file ag02581.dat & reduced using program C06.01 File sa7035.lft created using program C06.01 on Mon Feb 02 15:11:35 1998 :::::::::::::: SA7036A.LFT :::::::::::::: Airfoil: SA7036 (A) Builder: D. Thompson Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 99979 Number of angles of attack: 59 alpha / Cl / Cm -8.77 -0.497 0.0350 -8.04 -0.482 0.0218 -6.88 -0.429 -0.0181 -5.90 -0.349 -0.0503 -4.67 -0.248 -0.0518 -3.83 -0.186 -0.0510 -2.75 -0.089 -0.0532 -1.72 0.004 -0.0507 -0.68 0.151 -0.0603 0.30 0.319 -0.0741 1.44 0.477 -0.0831 2.35 0.568 -0.0793 3.47 0.660 -0.0723 4.38 0.738 -0.0676 5.35 0.817 -0.0635 6.42 0.907 -0.0599 7.55 1.003 -0.0575 8.41 1.076 -0.0555 9.58 1.165 -0.0497 10.46 1.194 -0.0439 11.55 1.209 -0.0377 12.56 1.216 -0.0366 13.64 1.222 -0.0429 14.48 1.222 -0.1325 16.00 1.047 -0.1519 16.29 1.001 -0.1576 17.51 1.051 -0.1709 18.50 1.005 -0.1686 19.33 1.024 -0.1678 20.37 1.068 -0.1707 19.60 1.002 -0.1777 18.59 0.998 -0.1723 17.39 1.001 -0.1732 16.56 1.026 -0.1751 15.58 1.017 -0.1738 14.62 1.104 -0.1507 13.81 1.200 -0.0628 12.81 1.211 -0.0467 11.85 1.211 -0.0459 10.85 1.206 -0.0505 9.69 1.170 -0.0579 8.81 1.120 -0.0632 7.76 1.033 -0.0654 6.72 0.942 -0.0676 5.57 0.849 -0.0707 4.60 0.771 -0.0752 3.63 0.692 -0.0801 2.65 0.608 -0.0876 1.63 0.511 -0.0939 0.62 0.379 -0.0898 -0.48 0.217 -0.0742 -1.57 0.038 -0.0591 -2.56 -0.046 -0.0600 -3.50 -0.136 -0.0569 -4.55 -0.229 -0.0571 -5.54 -0.306 -0.0586 -6.52 -0.401 -0.0449 -7.60 -0.451 -0.0058 -8.50 -0.498 0.0176 Tabulated from data in file ag02628.dat & reduced using program C06.01 Average Reynolds #: 149932 Number of angles of attack: 59 alpha / Cl / Cm -9.05 -0.514 0.0406 -7.85 -0.482 0.0153 -6.92 -0.435 -0.0130 -5.87 -0.346 -0.0516 -4.71 -0.241 -0.0552 -3.44 -0.098 -0.0591 -2.84 -0.027 -0.0654 -1.66 0.122 -0.0777 -0.52 0.275 -0.0812 0.35 0.362 -0.0804 1.27 0.458 -0.0784 2.62 0.578 -0.0746 3.33 0.649 -0.0728 4.49 0.764 -0.0713 5.45 0.858 -0.0690 6.36 0.941 -0.0671 7.38 1.028 -0.0645 8.51 1.126 -0.0615 9.59 1.177 -0.0554 10.51 1.209 -0.0496 11.47 1.212 -0.0443 12.61 1.207 -0.0481 13.43 1.201 -0.0539 14.37 1.206 -0.1286 15.56 1.160 -0.1733 16.50 1.057 -0.1706 17.50 1.038 -0.1809 18.64 1.049 -0.1760 19.50 1.056 -0.1779 20.44 1.088 -0.1873 19.50 1.048 -0.1842 18.40 1.065 -0.1847 17.53 1.039 -0.1752 16.45 1.045 -0.1838 15.46 1.129 -0.1817 14.59 1.243 -0.1226 13.75 1.197 -0.0650 12.78 1.207 -0.0526 11.87 1.210 -0.0498 10.83 1.208 -0.0523 9.79 1.190 -0.0587 8.72 1.143 -0.0649 7.77 1.081 -0.0676 6.76 0.996 -0.0692 5.75 0.899 -0.0715 4.36 0.763 -0.0736 3.61 0.687 -0.0744 2.43 0.568 -0.0756 1.44 0.474 -0.0785 0.61 0.392 -0.0799 -0.61 0.267 -0.0816 -1.71 0.135 -0.0783 -2.51 0.019 -0.0698 -3.52 -0.105 -0.0578 -4.72 -0.228 -0.0535 -5.61 -0.311 -0.0551 -6.57 -0.411 -0.0369 -7.68 -0.473 0.0027 -8.50 -0.497 0.0251 Tabulated from data in file ag02634.dat & reduced using program C06.01 Average Reynolds #: 199869 Number of angles of attack: 59 alpha / Cl / Cm -9.07 -0.549 0.0393 -7.73 -0.508 0.0062 -6.83 -0.454 -0.0242 -5.63 -0.328 -0.0561 -4.74 -0.240 -0.0565 -3.64 -0.107 -0.0646 -2.52 0.058 -0.0799 -1.52 0.170 -0.0834 -0.55 0.261 -0.0795 0.37 0.350 -0.0771 1.43 0.456 -0.0750 2.69 0.589 -0.0733 3.42 0.664 -0.0721 4.58 0.779 -0.0704 5.52 0.871 -0.0687 6.61 0.971 -0.0668 7.60 1.057 -0.0649 8.59 1.128 -0.0610 9.58 1.170 -0.0548 10.65 1.200 -0.0476 11.42 1.201 -0.0451 12.51 1.193 -0.0505 13.42 1.196 -0.0627 14.44 1.228 -0.1343 15.41 1.169 -0.1515 16.35 1.075 -0.1694 17.20 1.058 -0.1755 18.57 1.045 -0.1814 19.23 1.024 -0.1792 20.26 1.041 -0.1791 19.49 1.036 -0.1836 18.36 1.057 -0.1829 17.47 1.012 -0.1816 16.39 1.065 -0.1845 15.55 1.202 -0.1406 14.61 1.167 -0.1188 13.77 1.196 -0.0677 12.83 1.198 -0.0557 11.87 1.203 -0.0471 10.61 1.199 -0.0488 9.77 1.183 -0.0544 8.73 1.140 -0.0614 7.71 1.066 -0.0655 6.68 0.980 -0.0688 5.67 0.880 -0.0703 4.67 0.782 -0.0718 3.59 0.678 -0.0731 2.23 0.545 -0.0745 1.48 0.468 -0.0759 0.52 0.369 -0.0775 -0.53 0.271 -0.0799 -1.63 0.166 -0.0838 -2.54 0.055 -0.0797 -3.62 -0.097 -0.0657 -4.63 -0.231 -0.0554 -5.78 -0.340 -0.0552 -6.61 -0.430 -0.0354 -7.58 -0.489 0.0002 -8.53 -0.517 0.0254 Tabulated from data in file ag02630.dat & reduced using program C06.01 Average Reynolds #: 299899 Number of angles of attack: 57 alpha / Cl / Cm -9.02 -0.527 0.0367 -7.90 -0.527 0.0047 -6.93 -0.466 -0.0316 -5.96 -0.363 -0.0590 -4.99 -0.225 -0.0695 -3.81 -0.069 -0.0805 -2.98 0.030 -0.0856 -1.91 0.139 -0.0858 -0.64 0.249 -0.0798 0.29 0.347 -0.0782 1.17 0.444 -0.0772 2.26 0.557 -0.0765 3.32 0.663 -0.0757 4.32 0.762 -0.0743 5.43 0.878 -0.0731 6.42 0.976 -0.0723 7.38 1.062 -0.0702 8.32 1.133 -0.0662 9.35 1.188 -0.0596 10.35 1.216 -0.0525 11.38 1.224 -0.0492 12.33 1.225 -0.0549 13.33 1.213 -0.0683 14.47 1.191 -0.0833 15.23 1.258 -0.1463 16.14 1.185 -0.1690 17.10 1.052 -0.1769 18.10 1.029 -0.1840 19.14 1.011 -0.1863 18.68 1.026 -0.1850 17.59 1.030 -0.1763 16.66 1.097 -0.1829 15.70 1.228 -0.1606 14.84 1.259 -0.1347 13.61 1.216 -0.0734 12.78 1.222 -0.0634 11.85 1.227 -0.0518 10.63 1.226 -0.0496 9.79 1.209 -0.0546 8.60 1.158 -0.0626 7.63 1.095 -0.0673 6.21 0.967 -0.0714 5.65 0.910 -0.0723 4.57 0.801 -0.0742 3.57 0.696 -0.0757 2.16 0.546 -0.0776 1.31 0.455 -0.0783 0.49 0.367 -0.0792 -0.47 0.272 -0.0798 -1.51 0.177 -0.0860 -2.48 0.087 -0.0881 -3.51 -0.027 -0.0844 -4.66 -0.181 -0.0742 -5.78 -0.327 -0.0659 -6.81 -0.456 -0.0353 -7.61 -0.503 -0.0092 -8.45 -0.541 0.0190 Tabulated from data in file ag02632.dat & reduced using program C06.01 File sa7036a.lft created using program C06.01 on Mon Feb 02 15:11:35 1998 :::::::::::::: SA7036B.LFT :::::::::::::: Airfoil: SA7036 (B) Builder: T. Foster Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 99946 Number of angles of attack: 59 alpha / Cl / Cm -8.93 -0.519 0.0335 -7.81 -0.495 0.0171 -6.92 -0.450 -0.0039 -5.81 -0.344 -0.0435 -4.77 -0.236 -0.0575 -3.50 -0.115 -0.0589 -2.69 -0.030 -0.0613 -1.60 0.075 -0.0619 -0.53 0.215 -0.0713 0.29 0.349 -0.0822 1.37 0.508 -0.0913 2.54 0.612 -0.0873 3.57 0.691 -0.0817 4.45 0.766 -0.0771 5.50 0.859 -0.0735 6.69 0.961 -0.0695 7.48 1.021 -0.0670 8.57 1.087 -0.0612 9.61 1.174 -0.0562 10.55 1.220 -0.0516 11.59 1.274 -0.0463 12.69 1.292 -0.0410 13.64 1.264 -0.0409 14.46 0.997 -0.1559 15.69 0.981 -0.1647 16.49 0.988 -0.1574 17.48 1.000 -0.1637 18.64 1.011 -0.1642 19.45 1.046 -0.1719 20.49 1.036 -0.1775 19.60 0.981 -0.1783 18.55 1.038 -0.1804 17.60 1.011 -0.1725 16.62 1.000 -0.1816 15.64 0.991 -0.1696 14.48 1.002 -0.1658 13.55 0.963 -0.1674 12.60 0.942 -0.1555 11.90 1.279 -0.0584 10.94 1.255 -0.0574 9.94 1.202 -0.0617 8.83 1.135 -0.0662 7.91 1.073 -0.0706 6.81 0.995 -0.0757 5.81 0.908 -0.0784 4.71 0.807 -0.0818 3.45 0.703 -0.0886 2.76 0.647 -0.0938 1.40 0.520 -0.1018 0.32 0.365 -0.0937 -0.42 0.248 -0.0831 -1.42 0.092 -0.0672 -2.42 0.003 -0.0661 -3.45 -0.107 -0.0620 -4.56 -0.214 -0.0600 -5.47 -0.296 -0.0595 -6.48 -0.411 -0.0321 -7.44 -0.452 -0.0017 -8.53 -0.481 0.0184 Tabulated from data in file ag02698.dat & reduced using program C06.01 Average Reynolds #: 150040 Number of angles of attack: 59 alpha / Cl / Cm -8.88 -0.471 0.0320 -7.82 -0.443 0.0098 -6.90 -0.442 -0.0065 -5.71 -0.331 -0.0472 -4.46 -0.186 -0.0614 -3.40 -0.063 -0.0665 -2.68 0.030 -0.0730 -1.55 0.179 -0.0840 -0.57 0.310 -0.0884 0.41 0.421 -0.0900 1.54 0.529 -0.0864 2.58 0.636 -0.0846 3.56 0.726 -0.0815 4.52 0.818 -0.0795 5.61 0.920 -0.0770 6.60 1.010 -0.0749 7.60 1.090 -0.0707 8.80 1.164 -0.0647 9.56 1.213 -0.0609 10.63 1.262 -0.0548 11.93 1.322 -0.0485 12.57 1.329 -0.0452 13.53 1.291 -0.0547 14.60 1.248 -0.0778 15.43 1.028 -0.1681 16.54 1.039 -0.1776 17.58 1.041 -0.1738 18.57 1.037 -0.1751 19.52 1.041 -0.1760 20.49 1.042 -0.1890 19.39 1.041 -0.1852 18.52 1.014 -0.1792 17.51 1.035 -0.1794 16.28 0.996 -0.1749 14.99 1.014 -0.1746 14.57 1.011 -0.1796 13.48 1.031 -0.1694 12.57 1.067 -0.1561 11.95 1.330 -0.0558 10.57 1.274 -0.0618 9.68 1.232 -0.0667 8.84 1.176 -0.0709 7.72 1.100 -0.0763 6.76 1.025 -0.0796 5.77 0.939 -0.0830 4.59 0.836 -0.0857 3.69 0.748 -0.0876 2.47 0.626 -0.0907 1.67 0.550 -0.0931 0.60 0.440 -0.0971 -0.58 0.314 -0.0978 -1.66 0.174 -0.0927 -2.43 0.071 -0.0844 -3.75 -0.097 -0.0706 -4.50 -0.187 -0.0658 -5.54 -0.300 -0.0622 -6.48 -0.406 -0.0347 -7.49 -0.456 -0.0029 -8.51 -0.475 0.0205 Tabulated from data in file ag02700.dat & reduced using program C06.01 Average Reynolds #: 199958 Number of angles of attack: 59 alpha / Cl / Cm -8.86 -0.517 0.0297 -7.77 -0.482 0.0103 -6.60 -0.439 -0.0212 -5.74 -0.344 -0.0536 -4.59 -0.185 -0.0675 -3.55 -0.037 -0.0787 -2.58 0.102 -0.0913 -1.60 0.215 -0.0968 -0.54 0.312 -0.0927 0.60 0.427 -0.0900 1.49 0.521 -0.0888 2.54 0.630 -0.0868 3.50 0.726 -0.0850 4.68 0.838 -0.0829 5.53 0.924 -0.0819 6.51 1.015 -0.0796 7.60 1.105 -0.0765 8.60 1.176 -0.0721 9.68 1.247 -0.0671 10.64 1.292 -0.0619 11.71 1.338 -0.0559 12.62 1.333 -0.0504 13.66 1.301 -0.0655 14.56 1.256 -0.0890 15.68 1.249 -0.1027 16.54 1.205 -0.1124 17.48 1.075 -0.1903 18.38 1.032 -0.1876 19.36 1.043 -0.1898 20.44 1.048 -0.1969 19.69 1.072 -0.1932 18.62 1.056 -0.1890 17.63 1.080 -0.1884 16.67 1.075 -0.1835 15.58 1.071 -0.1887 14.65 1.012 -0.1725 13.32 1.006 -0.1671 13.02 1.322 -0.0532 11.94 1.338 -0.0545 10.96 1.312 -0.0600 9.87 1.258 -0.0654 8.73 1.181 -0.0708 7.62 1.101 -0.0757 6.56 1.019 -0.0801 5.69 0.938 -0.0821 4.70 0.844 -0.0837 3.52 0.734 -0.0857 2.60 0.641 -0.0866 1.52 0.531 -0.0890 0.54 0.429 -0.0912 -0.51 0.325 -0.0936 -1.68 0.210 -0.0967 -2.53 0.110 -0.0924 -3.55 -0.040 -0.0797 -4.62 -0.188 -0.0674 -5.70 -0.327 -0.0581 -6.52 -0.426 -0.0271 -7.60 -0.482 0.0013 -8.45 -0.506 0.0196 Tabulated from data in file ag02702.dat & reduced using program C06.01 Average Reynolds #: 300009 Number of angles of attack: 59 alpha / Cl / Cm -8.73 -0.523 0.0245 -7.59 -0.497 -0.0028 -6.74 -0.432 -0.0307 -5.93 -0.302 -0.0681 -4.94 -0.150 -0.0840 -3.90 -0.015 -0.0927 -2.90 0.098 -0.0958 -1.88 0.201 -0.0959 -0.83 0.298 -0.0919 0.19 0.396 -0.0882 1.31 0.521 -0.0872 2.37 0.628 -0.0862 3.37 0.729 -0.0855 4.48 0.844 -0.0839 5.52 0.949 -0.0835 6.67 1.055 -0.0812 7.60 1.135 -0.0785 8.76 1.219 -0.0734 9.66 1.280 -0.0690 10.65 1.337 -0.0638 11.60 1.371 -0.0569 12.61 1.370 -0.0534 13.71 1.318 -0.0823 14.66 1.264 -0.1018 15.38 1.248 -0.1140 16.33 1.234 -0.1242 17.35 1.205 -0.1313 18.04 1.102 -0.1935 19.17 1.060 -0.2009 20.32 1.053 -0.1938 19.83 1.068 -0.1961 18.61 1.070 -0.1947 17.83 1.130 -0.1905 16.77 1.160 -0.1859 15.94 1.121 -0.1785 14.84 1.130 -0.1771 13.81 1.121 -0.1672 12.91 1.349 -0.0632 11.94 1.362 -0.0606 10.93 1.327 -0.0650 9.66 1.270 -0.0678 8.71 1.213 -0.0710 7.76 1.149 -0.0751 6.41 1.040 -0.0792 5.52 0.956 -0.0818 4.51 0.857 -0.0838 3.64 0.768 -0.0850 2.51 0.651 -0.0870 1.57 0.553 -0.0883 0.57 0.438 -0.0887 -0.41 0.340 -0.0900 -1.58 0.232 -0.0965 -2.38 0.154 -0.0979 -3.71 0.011 -0.0951 -4.47 -0.088 -0.0895 -5.64 -0.243 -0.0800 -6.56 -0.400 -0.0433 -7.52 -0.487 -0.0071 -8.40 -0.513 0.0166 Tabulated from data in file ag02704.dat & reduced using program C06.01 File sa7036b.lft created using program C06.01 on Mon Feb 02 15:11:35 1998 :::::::::::::: SA7038.LFT :::::::::::::: Airfoil: SA7038 Builder: T. Foster Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 99896 Number of angles of attack: 59 alpha / Cl / Cm -9.10 -0.445 0.0330 -8.04 -0.437 0.0211 -7.00 -0.432 -0.0022 -6.05 -0.373 -0.0249 -5.05 -0.248 -0.0604 -4.07 -0.156 -0.0640 -3.02 -0.048 -0.0675 -2.03 0.078 -0.0748 -1.00 0.189 -0.0796 0.10 0.346 -0.0907 1.00 0.469 -0.0934 2.02 0.571 -0.0913 3.15 0.670 -0.0856 4.13 0.761 -0.0812 5.20 0.864 -0.0773 6.15 0.942 -0.0747 7.23 1.036 -0.0719 8.23 1.104 -0.0684 9.36 1.191 -0.0634 10.36 1.260 -0.0576 11.26 1.262 -0.0506 12.27 1.285 -0.0448 13.24 1.273 -0.0427 14.28 1.265 -0.0469 15.17 1.075 -0.1652 16.25 1.047 -0.1783 17.21 1.070 -0.1742 18.20 1.053 -0.1734 19.21 1.034 -0.1764 20.31 1.032 -0.1793 19.06 1.066 -0.1860 18.35 1.055 -0.1925 17.32 1.047 -0.1831 16.40 1.127 -0.1859 15.35 1.069 -0.1732 14.37 1.092 -0.1602 13.43 1.095 -0.1568 12.42 1.094 -0.1445 11.47 1.284 -0.0630 10.53 1.275 -0.0619 9.52 1.227 -0.0674 8.21 1.138 -0.0728 7.54 1.078 -0.0756 6.23 0.973 -0.0794 5.49 0.908 -0.0815 4.39 0.812 -0.0853 3.46 0.730 -0.0895 2.26 0.619 -0.0975 1.39 0.528 -0.1022 0.28 0.388 -0.1027 -0.79 0.231 -0.0916 -1.83 0.111 -0.0846 -2.72 0.004 -0.0743 -3.76 -0.118 -0.0674 -4.77 -0.218 -0.0657 -5.77 -0.331 -0.0443 -6.81 -0.405 -0.0126 -7.76 -0.422 0.0081 -8.75 -0.448 0.0211 Tabulated from data in file ag02644.dat & reduced using program C06.01 Average Reynolds #: 149991 Number of angles of attack: 59 alpha / Cl / Cm -9.17 -0.479 0.0373 -8.18 -0.469 0.0256 -7.09 -0.428 0.0088 -6.01 -0.379 -0.0204 -4.99 -0.229 -0.0634 -3.92 -0.094 -0.0710 -3.06 0.028 -0.0807 -1.76 0.212 -0.0957 -0.82 0.296 -0.0908 0.04 0.376 -0.0889 1.23 0.485 -0.0846 2.15 0.582 -0.0843 3.11 0.681 -0.0827 4.21 0.793 -0.0807 5.19 0.887 -0.0787 6.27 0.995 -0.0759 7.25 1.079 -0.0730 8.46 1.175 -0.0694 9.37 1.245 -0.0655 10.28 1.285 -0.0596 11.33 1.302 -0.0515 12.67 1.296 -0.0461 13.38 1.282 -0.0472 14.24 1.252 -0.0509 15.01 1.101 -0.1645 16.31 1.052 -0.1817 17.18 1.066 -0.1851 18.27 1.031 -0.1843 19.14 1.030 -0.1848 20.09 1.048 -0.1872 19.28 1.055 -0.1903 18.30 1.044 -0.1916 17.22 1.051 -0.1905 16.36 1.059 -0.1848 15.30 1.146 -0.1796 14.69 1.257 -0.0652 13.53 1.277 -0.0560 12.53 1.294 -0.0525 11.38 1.304 -0.0570 10.52 1.294 -0.0635 9.52 1.259 -0.0703 8.59 1.191 -0.0748 7.52 1.105 -0.0780 6.30 0.998 -0.0820 5.47 0.915 -0.0832 4.42 0.814 -0.0854 3.16 0.701 -0.0884 2.33 0.614 -0.0900 1.36 0.502 -0.0905 0.36 0.406 -0.0937 -0.74 0.310 -0.0964 -1.75 0.220 -0.1019 -2.76 0.078 -0.0934 -3.81 -0.072 -0.0811 -4.83 -0.200 -0.0723 -5.85 -0.357 -0.0409 -6.88 -0.421 -0.0097 -7.76 -0.442 0.0115 -8.69 -0.453 0.0241 Tabulated from data in file ag02646.dat & reduced using program C06.01 Average Reynolds #: 199856 Number of angles of attack: 59 alpha / Cl / Cm -9.13 -0.496 0.0375 -8.05 -0.456 0.0203 -6.96 -0.434 -0.0047 -5.73 -0.288 -0.0547 -4.99 -0.167 -0.0774 -3.97 -0.019 -0.0884 -2.92 0.114 -0.0959 -1.79 0.229 -0.0975 -0.78 0.307 -0.0891 0.32 0.417 -0.0870 1.07 0.503 -0.0871 2.28 0.621 -0.0849 3.14 0.718 -0.0839 4.16 0.814 -0.0822 5.25 0.928 -0.0807 6.14 1.017 -0.0793 7.30 1.124 -0.0769 8.26 1.198 -0.0732 9.45 1.276 -0.0679 10.20 1.305 -0.0625 11.32 1.321 -0.0547 12.33 1.305 -0.0543 13.44 1.285 -0.0625 14.37 1.262 -0.0672 15.24 1.239 -0.0787 15.89 1.123 -0.1826 17.03 1.059 -0.1875 18.01 1.063 -0.1875 18.98 1.080 -0.1891 20.09 1.083 -0.1903 19.30 1.075 -0.1929 18.31 1.078 -0.1938 17.28 1.085 -0.1931 16.31 1.071 -0.1984 15.28 1.232 -0.1787 14.68 1.253 -0.0727 13.61 1.289 -0.0626 12.62 1.307 -0.0567 11.67 1.315 -0.0541 10.57 1.315 -0.0602 9.51 1.281 -0.0676 8.58 1.227 -0.0728 7.50 1.141 -0.0770 6.39 1.039 -0.0797 5.26 0.929 -0.0823 4.25 0.829 -0.0841 3.28 0.728 -0.0851 2.24 0.618 -0.0859 1.19 0.511 -0.0877 0.12 0.397 -0.0879 -0.94 0.289 -0.0920 -2.00 0.209 -0.0983 -2.89 0.119 -0.0956 -3.86 0.003 -0.0893 -4.91 -0.145 -0.0786 -5.85 -0.311 -0.0526 -6.76 -0.422 -0.0115 -7.74 -0.459 0.0150 -8.71 -0.488 0.0292 Tabulated from data in file ag02656.dat & reduced using program C06.01 Average Reynolds #: 299943 Number of angles of attack: 59 alpha / Cl / Cm -9.20 -0.491 0.0381 -8.11 -0.490 0.0175 -7.20 -0.449 -0.0105 -6.19 -0.309 -0.0627 -5.31 -0.153 -0.0916 -4.26 -0.029 -0.0969 -3.12 0.085 -0.0970 -2.15 0.175 -0.0947 -1.19 0.278 -0.0944 -0.05 0.383 -0.0893 0.97 0.498 -0.0883 2.07 0.611 -0.0876 3.05 0.711 -0.0865 4.08 0.817 -0.0859 5.23 0.939 -0.0852 6.17 1.034 -0.0837 7.37 1.147 -0.0810 8.42 1.234 -0.0772 9.47 1.302 -0.0713 10.34 1.336 -0.0648 11.29 1.352 -0.0580 12.22 1.338 -0.0577 13.47 1.317 -0.0680 14.30 1.289 -0.0748 15.39 1.261 -0.0922 15.88 1.195 -0.1881 16.83 1.079 -0.1894 17.88 1.058 -0.1918 18.85 1.049 -0.1937 19.89 1.069 -0.2019 19.45 1.059 -0.2008 18.40 1.047 -0.1960 17.46 1.052 -0.1958 16.65 1.103 -0.1921 15.63 1.239 -0.1811 14.45 1.285 -0.0778 13.46 1.307 -0.0709 12.60 1.335 -0.0634 11.59 1.347 -0.0567 10.61 1.343 -0.0611 9.43 1.300 -0.0694 8.50 1.239 -0.0744 7.44 1.158 -0.0782 6.24 1.048 -0.0813 5.21 0.947 -0.0836 4.09 0.827 -0.0852 3.24 0.738 -0.0865 2.15 0.621 -0.0885 1.10 0.510 -0.0899 0.30 0.422 -0.0903 -1.11 0.286 -0.0955 -1.76 0.218 -0.0963 -2.78 0.120 -0.0975 -3.81 0.021 -0.0989 -4.76 -0.080 -0.0967 -5.83 -0.237 -0.0831 -6.86 -0.413 -0.0244 -7.79 -0.477 0.0034 -8.63 -0.495 0.0261 Tabulated from data in file ag02659.dat & reduced using program C06.01 File sa7038.lft created using program C06.01 on Mon Feb 02 15:11:35 1998 :::::::::::::: SD7032T.LFT :::::::::::::: Airfoil: SD7032 (D) Builder: S. Watson Comment: Zigzag trip Type C (h = 0.023") @ 2% u.s. & 5% l.s. Number of Reynolds #'s: 3 Average Reynolds #: 100034 Number of angles of attack: 59 alpha / Cl / Cm -8.79 -0.410 0.0343 -7.83 -0.395 0.0158 -6.91 -0.381 -0.0033 -5.97 -0.343 -0.0319 -4.94 -0.225 -0.0665 -3.74 -0.070 -0.0778 -2.82 0.058 -0.0893 -1.65 0.222 -0.1041 -0.75 0.330 -0.1084 0.15 0.417 -0.1052 1.14 0.497 -0.0956 2.32 0.590 -0.0891 3.24 0.656 -0.0855 4.36 0.718 -0.0820 5.34 0.809 -0.0801 6.32 0.897 -0.0781 7.28 0.968 -0.0754 8.43 1.056 -0.0716 9.54 1.112 -0.0669 10.39 1.158 -0.0641 11.51 1.200 -0.0599 12.37 1.226 -0.0598 13.38 1.239 -0.0583 14.50 1.252 -0.0624 15.24 0.910 -0.1730 16.31 0.990 -0.1772 17.38 0.988 -0.1773 18.27 0.995 -0.1911 19.41 1.013 -0.1946 20.31 1.044 -0.2009 19.32 1.066 -0.2012 18.45 1.029 -0.2043 17.39 1.001 -0.1864 16.33 0.996 -0.1905 15.34 0.983 -0.1908 14.38 1.028 -0.1844 13.59 1.219 -0.0766 12.59 1.230 -0.0700 11.70 1.211 -0.0700 10.61 1.181 -0.0735 9.72 1.149 -0.0768 8.68 1.094 -0.0811 7.63 1.021 -0.0847 6.65 0.947 -0.0867 5.54 0.856 -0.0889 4.44 0.762 -0.0910 3.39 0.673 -0.0939 2.45 0.594 -0.0962 1.48 0.509 -0.1009 0.32 0.415 -0.1132 -0.59 0.335 -0.1194 -1.67 0.214 -0.1139 -2.86 0.035 -0.0985 -3.77 -0.107 -0.0857 -4.65 -0.215 -0.0764 -5.75 -0.358 -0.0570 -6.63 -0.421 -0.0248 -7.63 -0.465 -0.0008 -8.62 -0.491 0.0169 Tabulated from data in file pg02565.dat & reduced using program C06.01 Average Reynolds #: 199971 Number of angles of attack: 59 alpha / Cl / Cm -9.05 -0.440 0.0340 -7.95 -0.443 0.0176 -6.79 -0.403 -0.0146 -6.01 -0.280 -0.0647 -4.89 -0.097 -0.0956 -3.89 0.032 -0.1047 -2.62 0.169 -0.1071 -1.63 0.258 -0.1022 -0.65 0.349 -0.0989 0.14 0.427 -0.0973 1.42 0.545 -0.0959 2.36 0.630 -0.0946 3.48 0.729 -0.0931 4.60 0.836 -0.0918 5.49 0.915 -0.0900 6.37 0.988 -0.0871 7.53 1.073 -0.0828 8.35 1.127 -0.0795 9.57 1.188 -0.0738 10.49 1.219 -0.0697 11.39 1.237 -0.0686 12.46 1.262 -0.0729 13.49 1.277 -0.0773 14.55 1.279 -0.0877 15.84 1.274 -0.1034 16.41 1.294 -0.1088 17.55 1.282 -0.1201 18.20 1.084 -0.1792 19.08 1.099 -0.2031 20.09 1.115 -0.2042 19.39 1.097 -0.2047 18.57 1.088 -0.2026 17.62 1.103 -0.1895 16.49 1.149 -0.1860 15.48 1.060 -0.1823 14.61 1.219 -0.1515 13.48 1.277 -0.0808 12.45 1.267 -0.0750 11.53 1.241 -0.0715 10.59 1.227 -0.0715 9.63 1.193 -0.0745 8.55 1.139 -0.0792 7.60 1.081 -0.0836 6.54 1.006 -0.0881 5.16 0.890 -0.0926 4.50 0.832 -0.0942 3.43 0.731 -0.0957 2.18 0.615 -0.0961 1.19 0.526 -0.0974 0.19 0.438 -0.0984 -1.03 0.315 -0.1004 -2.41 0.191 -0.1086 -2.66 0.169 -0.1085 -3.87 0.037 -0.1060 -4.87 -0.090 -0.0975 -5.89 -0.250 -0.0738 -6.74 -0.400 -0.0195 -7.65 -0.438 0.0110 -8.66 -0.462 0.0271 Tabulated from data in file pg02567.dat & reduced using program C06.01 Average Reynolds #: 299868 Number of angles of attack: 53 alpha / Cl / Cm -6.19 -0.243 -0.0847 -5.16 -0.101 -0.1032 -4.09 0.015 -0.1051 -2.80 0.129 -0.1006 -2.03 0.209 -0.1014 -0.99 0.318 -0.1014 0.04 0.417 -0.1001 0.99 0.514 -0.0997 2.14 0.625 -0.0989 3.48 0.755 -0.0977 4.09 0.815 -0.0973 5.23 0.919 -0.0953 6.30 1.009 -0.0920 7.29 1.091 -0.0887 8.80 1.182 -0.0813 9.69 1.223 -0.0762 10.84 1.263 -0.0720 11.66 1.276 -0.0741 12.73 1.316 -0.0764 13.61 1.329 -0.0959 14.35 1.310 -0.1035 15.15 1.293 -0.1161 16.15 1.282 -0.1273 17.17 1.279 -0.1378 18.11 1.266 -0.1543 19.02 1.304 -0.1690 20.03 1.378 -0.2006 19.71 1.383 -0.1894 18.72 1.343 -0.1909 17.75 1.337 -0.1734 17.10 1.341 -0.1415 15.43 1.329 -0.1107 14.44 1.347 -0.0971 13.46 1.330 -0.0874 12.58 1.310 -0.0772 11.64 1.281 -0.0725 10.64 1.261 -0.0723 9.67 1.225 -0.0753 8.07 1.144 -0.0830 7.23 1.087 -0.0871 6.49 1.031 -0.0892 5.45 0.944 -0.0928 4.47 0.854 -0.0949 3.28 0.740 -0.0974 2.51 0.665 -0.0984 1.53 0.565 -0.1000 0.48 0.464 -0.1012 -0.74 0.342 -0.1025 -1.53 0.265 -0.1029 -2.62 0.151 -0.1026 -3.63 0.059 -0.1056 -4.61 -0.036 -0.1066 -5.66 -0.149 -0.1028 Tabulated from data in file pg02569.dat & reduced using program C06.01 File sd7032t.lft created using program C06.01 on Mon Feb 02 15:11:35 1998 :::::::::::::: SD7037BT.LFT :::::::::::::: Airfoil: SD7037 (B) Builder: D. Thompson Comment: Zigzag trip Type C (h = 0.023") @ 2% u.s. & 5% l.s. Number of Reynolds #'s: 3 Average Reynolds #: 99914 Number of angles of attack: 59 alpha / Cl / Cm -9.08 -0.525 0.0482 -8.06 -0.517 0.0442 -7.07 -0.503 0.0325 -5.98 -0.450 0.0052 -4.87 -0.361 -0.0450 -4.06 -0.280 -0.0519 -2.76 -0.173 -0.0527 -1.97 -0.092 -0.0545 -1.01 0.024 -0.0614 0.21 0.205 -0.0784 1.14 0.335 -0.0878 2.23 0.443 -0.0855 3.28 0.537 -0.0785 4.34 0.619 -0.0732 5.13 0.681 -0.0693 6.18 0.773 -0.0671 7.23 0.852 -0.0648 8.32 0.928 -0.0626 9.25 1.003 -0.0595 10.42 1.077 -0.0554 11.42 1.142 -0.0528 12.26 1.189 -0.0498 13.27 1.214 -0.0474 14.25 1.003 -0.1535 15.21 0.912 -0.1628 16.29 0.905 -0.1570 17.21 0.915 -0.1652 18.11 0.904 -0.1692 19.53 0.938 -0.1750 20.22 1.003 -0.1816 19.47 0.949 -0.1772 18.50 0.879 -0.1742 17.40 0.983 -0.1755 16.62 0.949 -0.1666 15.54 0.901 -0.1730 14.61 1.026 -0.1637 13.63 1.031 -0.1527 12.62 1.197 -0.0618 11.75 1.164 -0.0589 10.72 1.110 -0.0625 9.68 1.035 -0.0651 8.67 0.967 -0.0683 7.51 0.883 -0.0716 6.62 0.807 -0.0735 5.56 0.726 -0.0754 4.56 0.648 -0.0785 3.56 0.568 -0.0843 2.37 0.468 -0.0933 1.30 0.370 -0.0970 0.46 0.249 -0.0897 -0.54 0.087 -0.0751 -1.56 -0.048 -0.0642 -2.63 -0.153 -0.0602 -3.63 -0.240 -0.0589 -4.64 -0.328 -0.0571 -5.63 -0.426 -0.0342 -6.63 -0.488 0.0077 -7.59 -0.483 0.0251 -8.59 -0.544 0.0525 Tabulated from data in file pg02637.dat & reduced using program C06.01 Average Reynolds #: 201844 Number of angles of attack: 59 alpha / Cl / Cm -9.11 -0.548 0.0499 -8.12 -0.536 0.0425 -7.11 -0.501 0.0234 -5.71 -0.432 -0.0172 -4.93 -0.307 -0.0607 -3.96 -0.205 -0.0683 -2.88 -0.079 -0.0765 -1.86 0.046 -0.0828 -0.61 0.185 -0.0862 0.21 0.258 -0.0819 1.25 0.354 -0.0772 2.31 0.458 -0.0759 3.20 0.547 -0.0756 4.31 0.654 -0.0747 5.26 0.753 -0.0740 6.20 0.862 -0.0720 7.21 0.955 -0.0695 8.34 1.050 -0.0666 9.27 1.120 -0.0640 10.23 1.181 -0.0606 11.37 1.236 -0.0565 12.29 1.261 -0.0546 13.26 1.284 -0.0595 14.37 1.276 -0.0650 14.92 0.986 -0.1587 16.32 1.048 -0.1729 17.12 1.022 -0.1816 18.22 1.022 -0.1805 19.10 1.003 -0.1869 20.04 1.031 -0.1845 19.26 1.000 -0.1881 18.25 1.078 -0.1809 17.46 1.045 -0.1839 16.27 1.058 -0.1774 15.47 1.020 -0.1654 14.18 1.074 -0.1655 13.41 1.163 -0.1534 12.81 1.273 -0.0581 11.72 1.248 -0.0565 10.55 1.202 -0.0604 9.58 1.143 -0.0640 8.66 1.078 -0.0666 7.71 1.006 -0.0696 6.67 0.914 -0.0724 5.52 0.791 -0.0758 4.59 0.681 -0.0756 3.50 0.575 -0.0760 2.52 0.480 -0.0762 1.50 0.385 -0.0771 0.50 0.288 -0.0804 -0.73 0.178 -0.0865 -1.80 0.061 -0.0850 -2.71 -0.050 -0.0796 -3.64 -0.159 -0.0737 -4.87 -0.298 -0.0662 -5.60 -0.415 -0.0265 -6.64 -0.476 0.0094 -7.59 -0.499 0.0331 -8.60 -0.550 0.0468 Tabulated from data in file pg02639.dat & reduced using program C06.01 Average Reynolds #: 299744 Number of angles of attack: 59 alpha / Cl / Cm -9.11 -0.585 0.0533 -8.10 -0.567 0.0373 -7.11 -0.528 0.0179 -5.82 -0.434 -0.0318 -4.97 -0.290 -0.0734 -3.95 -0.178 -0.0791 -2.99 -0.072 -0.0824 -1.87 0.039 -0.0792 -0.68 0.149 -0.0757 0.27 0.249 -0.0753 1.13 0.374 -0.0757 2.66 0.566 -0.0761 3.38 0.642 -0.0764 4.25 0.734 -0.0759 5.31 0.841 -0.0745 6.37 0.942 -0.0728 7.69 1.058 -0.0690 8.37 1.113 -0.0662 9.30 1.176 -0.0619 10.27 1.234 -0.0569 11.37 1.277 -0.0529 12.39 1.301 -0.0600 13.48 1.312 -0.0685 14.43 1.316 -0.0822 15.31 1.249 -0.1011 16.04 1.072 -0.1787 17.10 1.097 -0.1851 18.07 1.018 -0.1797 18.95 1.031 -0.1945 19.94 1.065 -0.2019 19.54 1.049 -0.1941 18.52 1.034 -0.1844 17.61 1.052 -0.1807 16.54 1.122 -0.1818 15.64 1.056 -0.1769 14.65 1.089 -0.1691 13.50 1.180 -0.1537 12.64 1.294 -0.0776 11.69 1.268 -0.0758 10.53 1.217 -0.0755 9.74 1.176 -0.0753 8.63 1.138 -0.0652 7.70 1.075 -0.0681 6.67 0.991 -0.0710 5.57 0.890 -0.0723 4.48 0.782 -0.0742 3.24 0.653 -0.0759 2.52 0.576 -0.0762 1.36 0.449 -0.0764 0.38 0.330 -0.0762 -0.81 0.154 -0.0755 -1.74 0.063 -0.0782 -2.69 -0.026 -0.0840 -3.71 -0.148 -0.0808 -4.67 -0.268 -0.0757 -5.68 -0.429 -0.0307 -6.62 -0.518 0.0131 -7.56 -0.542 0.0371 -8.50 -0.553 0.0489 Tabulated from data in file pg02641.dat & reduced using program C06.01 File sd7037bt.lft created using program C06.01 on Mon Feb 02 15:11:35 1998 :::::::::::::: SD7037D.LFT :::::::::::::: Airfoil: SD7037 (D) Builder: H. Stokely / B. Williams Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 59200 Number of angles of attack: 49 alpha / Cl / Cm -5.75 -0.315 -0.0573 -4.57 -0.228 -0.0569 -3.40 -0.166 -0.0531 -2.25 -0.087 -0.0515 -1.61 -0.036 -0.0446 -0.43 0.053 -0.0498 0.74 0.202 -0.0579 1.40 0.328 -0.0652 2.63 0.502 -0.0802 3.84 0.626 -0.0771 4.49 0.676 -0.0723 5.71 0.778 -0.0659 6.91 0.882 -0.0601 7.54 0.935 -0.0564 8.73 1.027 -0.0509 9.89 1.109 -0.0462 11.02 1.167 -0.0409 11.64 1.180 -0.0375 12.79 1.188 -0.0344 13.87 0.923 -0.1213 14.51 0.931 -0.1353 15.75 0.920 -0.1369 16.96 0.963 -0.1505 17.62 0.950 -0.1529 18.85 0.970 -0.1588 16.73 0.922 -0.1467 15.64 0.932 -0.1425 15.04 0.955 -0.1445 13.93 0.883 -0.1295 12.86 0.852 -0.1220 11.88 1.151 -0.0537 10.87 1.165 -0.0415 9.81 1.063 -0.0483 8.77 1.052 -0.0547 7.66 0.957 -0.0573 6.56 0.867 -0.0668 5.97 0.816 -0.0679 4.87 0.720 -0.0748 3.75 0.620 -0.0870 2.63 0.500 -0.0959 1.52 0.344 -0.0864 0.44 0.188 -0.0700 -0.14 0.120 -0.0573 -1.21 0.024 -0.0517 -2.25 -0.052 -0.0562 -3.30 -0.131 -0.0560 -4.36 -0.206 -0.0580 -5.46 -0.279 -0.0596 -6.58 -0.363 -0.0454 Tabulated from data in file AB01099.DAT & reduced using program Q06.01L Average Reynolds #: 99100 Number of angles of attack: 49 alpha / Cl / Cm -5.93 -0.398 -0.0475 -4.22 -0.245 -0.0530 -3.60 -0.192 -0.0533 -2.40 -0.071 -0.0556 -1.26 0.068 -0.0577 -0.63 0.176 -0.0658 1.05 0.405 -0.0806 1.28 0.427 -0.0803 3.08 0.593 -0.0764 3.77 0.652 -0.0719 5.00 0.763 -0.0670 5.64 0.822 -0.0642 6.87 0.928 -0.0603 7.49 0.982 -0.0587 8.63 1.077 -0.0551 9.79 1.146 -0.0488 10.94 1.189 -0.0420 12.06 1.201 -0.0358 12.65 1.194 -0.0338 13.74 1.011 -0.1275 14.90 0.958 -0.1318 15.55 1.009 -0.1457 16.76 1.002 -0.1490 17.97 0.983 -0.1510 18.62 0.985 -0.1527 16.46 1.009 -0.1589 15.88 1.017 -0.1567 14.72 0.990 -0.1444 13.61 0.991 -0.1318 13.08 1.178 -0.0443 12.05 1.192 -0.0387 11.02 1.183 -0.0443 9.99 1.149 -0.0501 8.94 1.091 -0.0549 7.87 1.012 -0.0583 6.79 0.918 -0.0599 5.69 0.820 -0.0626 4.60 0.719 -0.0657 3.99 0.666 -0.0683 2.88 0.566 -0.0748 1.74 0.461 -0.0803 0.55 0.342 -0.0787 -0.52 0.197 -0.0680 -1.13 0.099 -0.0598 -2.71 -0.099 -0.0507 -3.29 -0.159 -0.0497 -4.38 -0.268 -0.0484 -5.46 -0.354 -0.0497 -6.60 -0.460 -0.0236 Tabulated from data in file AB01101.DAT & reduced using program Q06.01L Average Reynolds #: 197400 Number of angles of attack: 49 alpha / Cl / Cm -5.88 -0.391 -0.0461 -4.71 -0.244 -0.0603 -3.53 -0.089 -0.0697 -2.37 0.069 -0.0801 -1.58 0.142 -0.0809 -0.34 0.247 -0.0720 0.83 0.371 -0.0699 1.46 0.442 -0.0706 2.64 0.569 -0.0685 3.73 0.687 -0.0655 4.93 0.807 -0.0626 5.60 0.873 -0.0612 6.80 0.984 -0.0591 7.95 1.085 -0.0558 8.57 1.134 -0.0541 9.73 1.206 -0.0487 10.84 1.250 -0.0418 11.94 1.250 -0.0357 13.01 1.235 -0.0387 13.60 1.230 -0.0484 14.46 1.101 -0.1401 16.03 1.066 -0.1542 16.57 1.066 -0.1544 17.63 1.085 -0.1575 18.68 1.050 -0.1555 16.42 1.069 -0.1554 15.77 1.069 -0.1549 14.61 1.079 -0.1443 13.72 1.213 -0.0537 13.13 1.231 -0.0451 11.69 1.260 -0.0384 11.11 1.258 -0.0417 10.08 1.224 -0.0469 9.04 1.166 -0.0521 7.98 1.087 -0.0562 6.88 0.994 -0.0595 5.74 0.888 -0.0620 4.59 0.775 -0.0642 3.93 0.710 -0.0661 2.84 0.592 -0.0688 1.75 0.471 -0.0713 0.05 0.281 -0.0718 0.24 0.301 -0.0700 -1.37 0.155 -0.0809 -2.69 0.025 -0.0793 -3.34 -0.075 -0.0708 -4.49 -0.231 -0.0584 -5.69 -0.367 -0.0534 -6.36 -0.453 -0.0341 Tabulated from data in file PG01103.DAT & reduced using program Q06.01L Average Reynolds #: 296000 Number of angles of attack: 49 alpha / Cl / Cm -6.02 -0.370 -0.0631 -4.63 -0.188 -0.0756 -3.69 -0.076 -0.0798 -2.74 0.028 -0.0800 -1.60 0.118 -0.0779 -0.63 0.228 -0.0757 0.85 0.386 -0.0693 1.43 0.455 -0.0688 2.54 0.574 -0.0673 3.70 0.696 -0.0660 4.86 0.815 -0.0643 5.48 0.876 -0.0633 6.69 0.993 -0.0619 7.95 1.104 -0.0586 8.63 1.156 -0.0561 9.84 1.236 -0.0506 11.00 1.275 -0.0421 11.64 1.274 -0.0385 12.75 1.251 -0.0453 13.84 1.220 -0.0664 14.86 1.192 -0.0780 15.82 1.173 -0.0906 16.51 1.189 -0.1492 17.80 1.163 -0.1636 18.61 1.133 -0.1654 16.66 1.196 -0.1508 15.63 1.177 -0.1414 15.04 1.220 -0.1355 14.26 1.206 -0.0739 12.79 1.258 -0.0473 11.85 1.276 -0.0368 10.85 1.277 -0.0414 9.84 1.238 -0.0480 8.80 1.168 -0.0530 7.73 1.086 -0.0578 6.60 0.983 -0.0599 5.93 0.914 -0.0615 4.78 0.806 -0.0635 3.58 0.688 -0.0651 2.30 0.550 -0.0674 1.64 0.479 -0.0683 0.49 0.354 -0.0703 -0.15 0.289 -0.0710 -1.62 0.129 -0.0783 -2.19 0.070 -0.0801 -3.37 -0.044 -0.0801 -4.40 -0.168 -0.0767 -5.44 -0.292 -0.0707 -6.41 -0.453 -0.0439 Tabulated from data in file PG01105.DAT & reduced using program Q06.01L File SD7037D.LFT created on 10-24-1997 at 19:34:42 using program FORMAT :::::::::::::: SD7037D2.LFT :::::::::::::: Airfoil: SD7037 (D) Builder: H. Stokely / B. Williams Comment: with upper surface covering Number of Reynolds #'s: 1 Average Reynolds #: 197500 Number of angles of attack: 49 alpha / Cl / Cm -5.99 -0.422 -0.0384 -4.51 -0.252 -0.0571 -3.48 -0.112 -0.0652 -2.58 0.006 -0.0740 -1.68 0.121 -0.0797 -0.15 0.258 -0.0699 0.38 0.311 -0.0680 1.71 0.459 -0.0680 2.66 0.556 -0.0663 3.66 0.655 -0.0640 4.61 0.749 -0.0622 5.55 0.842 -0.0605 6.93 0.973 -0.0588 7.86 1.056 -0.0559 8.73 1.125 -0.0530 9.57 1.182 -0.0496 10.85 1.242 -0.0422 11.67 1.256 -0.0367 12.91 1.243 -0.0346 13.72 1.220 -0.0459 14.98 1.181 -0.0636 15.58 1.041 -0.1464 16.89 1.053 -0.1520 17.76 1.076 -0.1576 18.56 1.081 -0.1566 16.80 1.060 -0.1544 15.87 1.081 -0.1520 15.00 1.083 -0.1450 13.90 1.235 -0.0493 13.07 1.244 -0.0378 11.95 1.262 -0.0376 11.16 1.257 -0.0421 10.01 1.208 -0.0495 8.78 1.129 -0.0549 7.94 1.060 -0.0577 6.70 0.949 -0.0614 5.83 0.870 -0.0632 4.85 0.775 -0.0650 3.89 0.682 -0.0669 2.60 0.553 -0.0696 1.65 0.457 -0.0715 0.68 0.344 -0.0704 -0.30 0.247 -0.0736 -1.21 0.174 -0.0821 -2.53 0.015 -0.0760 -3.45 -0.105 -0.0676 -4.45 -0.238 -0.0594 -5.45 -0.346 -0.0556 -6.36 -0.447 -0.0249 Tabulated from data in file CL02017.DAT & reduced using program Q06.01L File SD7037D2.LFT created on 10-24-1997 at 19:34:42 using program FORMAT :::::::::::::: SD7062B.LFT :::::::::::::: Airfoil: SD7062 (B) Builder: Widiner / M. Allen Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 60300 Number of angles of attack: 49 alpha / Cl / Cm -5.27 -0.255 -0.0549 -3.97 -0.127 -0.0664 -2.65 0.017 -0.0848 -1.97 0.075 -0.0887 -0.51 0.196 -0.0969 0.17 0.237 -0.0906 1.48 0.351 -0.1008 2.15 0.408 -0.0992 3.47 0.501 -0.1078 4.14 0.527 -0.1032 5.49 0.565 -0.1093 6.17 0.608 -0.1077 7.50 0.623 -0.1141 8.31 0.654 -0.1115 9.60 0.694 -0.1193 10.27 0.702 -0.1181 11.62 0.763 -0.1314 12.34 0.761 -0.1220 13.68 0.802 -0.1375 14.42 0.845 -0.1335 15.75 0.888 -0.1505 16.50 0.886 -0.1377 17.25 0.916 -0.1417 18.65 0.990 -0.1675 19.37 1.038 -0.1608 17.56 0.963 -0.1484 16.25 0.890 -0.1395 15.57 0.878 -0.1416 14.29 0.865 -0.1359 13.63 0.838 -0.1401 12.38 0.794 -0.1305 11.18 0.737 -0.1250 10.55 0.733 -0.1258 9.34 0.693 -0.1210 8.19 0.673 -0.1188 7.58 0.669 -0.1214 6.40 0.665 -0.1167 5.63 0.652 -0.1139 4.42 0.558 -0.1153 3.24 0.511 -0.1104 2.61 0.505 -0.1151 1.45 0.410 -0.1087 0.30 0.303 -0.1012 -0.85 0.199 -0.0964 -1.46 0.163 -0.1000 -2.62 0.029 -0.0896 -3.80 -0.095 -0.0750 -4.97 -0.209 -0.0671 -5.63 -0.263 -0.0594 Tabulated from data in file PG01720.DAT & reduced using program Q06.01L Average Reynolds #: 100400 Number of angles of attack: 49 alpha / Cl / Cm -5.17 -0.121 -0.0875 -3.91 0.035 -0.1025 -2.68 0.174 -0.1106 -1.81 0.266 -0.1076 -0.92 0.349 -0.1015 0.31 0.466 -0.0942 1.18 0.574 -0.0961 2.41 0.698 -0.0965 3.30 0.787 -0.0972 4.18 0.873 -0.0968 5.43 0.975 -0.0940 6.31 1.048 -0.0943 7.56 1.154 -0.0914 8.41 1.227 -0.0919 9.59 1.322 -0.0888 10.42 1.387 -0.0881 11.59 1.451 -0.0841 12.42 1.484 -0.0806 13.60 1.516 -0.0747 14.24 0.898 -0.1453 15.48 0.926 -0.1511 16.36 0.980 -0.1622 17.21 0.990 -0.1631 18.50 1.029 -0.1721 19.37 1.043 -0.1778 17.41 0.996 -0.1674 16.57 0.976 -0.1647 15.80 0.969 -0.1636 14.66 0.910 -0.1507 13.56 0.882 -0.1473 12.51 0.877 -0.1456 11.44 0.862 -0.1388 10.40 0.901 -0.1374 9.75 1.325 -0.0971 8.72 1.245 -0.0938 7.67 1.160 -0.0950 6.58 1.067 -0.0958 5.48 0.972 -0.0965 4.72 0.911 -0.0975 3.62 0.817 -0.0981 2.57 0.710 -0.0985 1.52 0.602 -0.0990 0.47 0.482 -0.0969 -0.56 0.382 -0.1003 -1.59 0.291 -0.1094 -2.63 0.184 -0.1127 -3.70 0.062 -0.1071 -4.79 -0.068 -0.0973 -5.53 -0.163 -0.0891 Tabulated from data in file CF01154.DAT & reduced using program Q06.01L Average Reynolds #: 201300 Number of angles of attack: 49 alpha / Cl / Cm -5.23 -0.068 -0.0942 -3.86 0.053 -0.0949 -2.95 0.149 -0.0964 -1.59 0.290 -0.0974 -0.65 0.387 -0.0959 0.27 0.477 -0.0939 1.18 0.559 -0.0900 2.50 0.706 -0.0927 3.56 0.806 -0.0932 4.56 0.897 -0.0929 5.48 0.987 -0.0923 6.41 1.076 -0.0918 7.33 1.158 -0.0907 8.49 1.278 -0.0883 9.37 1.353 -0.0858 10.62 1.448 -0.0815 11.47 1.502 -0.0775 12.68 1.564 -0.0709 13.52 1.592 -0.0666 14.72 1.617 -0.0620 15.57 1.629 -0.0604 16.41 1.625 -0.0599 17.63 1.624 -0.0641 18.47 1.616 -0.0711 19.43 1.037 -0.1766 17.14 1.003 -0.1720 16.60 0.984 -0.1685 15.26 0.933 -0.1595 14.33 0.906 -0.1557 13.42 0.911 -0.1516 12.54 0.931 -0.1485 11.79 1.514 -0.0769 10.71 1.451 -0.0819 9.27 1.349 -0.0866 8.78 1.316 -0.0881 7.76 1.217 -0.0906 6.62 1.102 -0.0900 5.77 1.029 -0.0920 4.55 0.900 -0.0900 3.34 0.762 -0.0875 2.31 0.684 -0.0898 1.50 0.600 -0.0890 0.33 0.464 -0.0879 -0.46 0.413 -0.0955 -1.65 0.261 -0.0926 -2.82 0.129 -0.0913 -3.68 0.079 -0.0929 -4.92 -0.077 -0.0895 -5.83 -0.119 -0.0934 Tabulated from data in file PG01156.DAT & reduced using program Q06.01L Average Reynolds #: 301300 Number of angles of attack: 49 alpha / Cl / Cm -5.32 -0.103 -0.0940 -3.73 0.053 -0.0974 -2.62 0.178 -0.0999 -1.95 0.250 -0.1002 -0.64 0.368 -0.1011 0.48 0.502 -0.1002 1.48 0.620 -0.0966 2.20 0.696 -0.0959 3.47 0.836 -0.0970 4.79 0.974 -0.0976 5.60 1.054 -0.0971 6.33 1.127 -0.0966 7.67 1.252 -0.0948 8.38 1.317 -0.0936 9.60 1.414 -0.0897 10.83 1.500 -0.0841 11.48 1.536 -0.0806 12.62 1.591 -0.0743 13.78 1.623 -0.0686 14.41 1.637 -0.0673 15.61 1.654 -0.0674 16.88 1.662 -0.0698 17.56 1.660 -0.0723 18.85 1.649 -0.0797 19.49 1.641 -0.0840 17.54 1.660 -0.0733 16.52 1.661 -0.0687 15.53 1.646 -0.0676 14.53 1.634 -0.0675 13.51 1.613 -0.0698 12.48 1.584 -0.0744 11.41 1.532 -0.0794 10.80 1.497 -0.0826 9.71 1.421 -0.0875 8.58 1.329 -0.0909 7.40 1.225 -0.0939 6.73 1.161 -0.0949 5.46 1.035 -0.0958 4.18 0.906 -0.0965 3.46 0.831 -0.0968 2.14 0.681 -0.0953 1.39 0.611 -0.0976 0.31 0.494 -0.1005 -0.93 0.348 -0.1007 -1.80 0.264 -0.1000 -2.50 0.188 -0.0994 -3.75 0.059 -0.0965 -5.00 -0.076 -0.0948 -5.69 -0.141 -0.0942 Tabulated from data in file PG01159.DAT & reduced using program Q06.01L Average Reynolds #: 401400 Number of angles of attack: 49 alpha / Cl / Cm -5.85 -0.158 -0.0917 -3.88 0.037 -0.0958 -3.00 0.132 -0.0974 -1.94 0.233 -0.0991 -0.85 0.383 -0.1007 0.09 0.488 -0.1008 1.50 0.645 -0.0994 2.42 0.740 -0.0975 3.45 0.853 -0.0980 4.51 0.968 -0.0984 5.57 1.076 -0.0989 6.66 1.178 -0.0973 7.31 1.242 -0.0972 8.45 1.342 -0.0947 9.60 1.433 -0.0908 10.87 1.521 -0.0855 11.60 1.557 -0.0807 12.93 1.609 -0.0739 13.64 1.630 -0.0707 14.83 1.646 -0.0775 15.47 1.652 -0.0786 16.64 1.663 -0.0827 17.81 1.649 -0.0870 18.43 1.647 -0.0901 19.85 1.615 -0.0976 17.25 1.664 -0.0859 16.24 1.663 -0.0814 15.67 1.662 -0.0802 14.68 1.644 -0.0769 13.66 1.633 -0.0713 12.75 1.604 -0.0677 11.75 1.564 -0.0720 10.71 1.507 -0.0777 9.59 1.431 -0.0832 8.36 1.334 -0.0889 7.61 1.269 -0.0906 6.27 1.140 -0.0933 5.53 1.071 -0.0948 4.25 0.938 -0.0958 3.52 0.860 -0.0963 2.30 0.727 -0.0962 1.17 0.606 -0.0992 0.51 0.534 -0.0999 -0.59 0.411 -0.1001 -1.50 0.292 -0.0994 -3.12 0.122 -0.0969 -3.73 0.052 -0.0957 -4.76 -0.044 -0.0939 -5.76 -0.146 -0.0913 Tabulated from data in file PG01161.DAT & reduced using program Q06.01L File SD7062B.LFT created on 10-24-1997 at 19:34:42 using program FORMAT :::::::::::::: SD7062BT.LFT :::::::::::::: Airfoil: SD7062 (B) Builder: Widiner / M. Allen Comment: Zig-Zag trip type "C" @ u.s. x/c=2% & l.s. x/c=5% (h = 0.023") Number of Reynolds #'s: 4 Average Reynolds #: 100600 Number of angles of attack: 49 alpha / Cl / Cm -5.20 -0.186 -0.0887 -3.77 0.010 -0.1036 -2.39 0.165 -0.1094 -1.59 0.245 -0.1087 -0.79 0.319 -0.1072 0.59 0.438 -0.1027 1.39 0.505 -0.0961 2.17 0.570 -0.0905 3.58 0.713 -0.0879 4.40 0.803 -0.0861 5.82 0.934 -0.0848 6.61 1.003 -0.0840 7.36 1.054 -0.0802 8.72 1.140 -0.0769 9.49 1.179 -0.0732 10.84 1.222 -0.0691 11.59 1.218 -0.0676 12.32 1.208 -0.0706 13.67 1.206 -0.0797 14.42 1.190 -0.0821 15.79 1.173 -0.0924 16.60 1.173 -0.0971 17.38 1.184 -0.1008 18.75 1.217 -0.1073 19.48 1.252 -0.1073 17.66 1.204 -0.0965 16.39 1.205 -0.0909 15.69 1.194 -0.0899 14.40 1.188 -0.0840 13.71 1.179 -0.0789 12.49 1.201 -0.0714 11.28 1.218 -0.0695 10.64 1.217 -0.0705 9.38 1.177 -0.0753 8.69 1.145 -0.0799 7.42 1.064 -0.0831 6.75 1.020 -0.0870 5.48 0.920 -0.0896 4.14 0.788 -0.0916 3.41 0.710 -0.0924 2.10 0.579 -0.0935 1.44 0.522 -0.1010 0.19 0.415 -0.1085 -0.54 0.352 -0.1105 -1.77 0.236 -0.1126 -2.52 0.162 -0.1118 -3.78 0.020 -0.1051 -4.55 -0.095 -0.0978 -5.87 -0.253 -0.0798 Tabulated from data in file PG01743.DAT & reduced using program Q06.01L Average Reynolds #: 201100 Number of angles of attack: 49 alpha / Cl / Cm -5.24 -0.091 -0.1002 -3.72 0.044 -0.0997 -2.69 0.145 -0.0987 -1.66 0.251 -0.0972 -0.66 0.359 -0.0972 0.32 0.458 -0.0954 1.34 0.564 -0.0950 2.34 0.661 -0.0941 3.35 0.753 -0.0931 4.38 0.841 -0.0911 5.40 0.921 -0.0890 6.41 0.990 -0.0845 7.41 1.059 -0.0812 8.39 1.120 -0.0775 9.31 1.159 -0.0735 10.65 1.186 -0.0739 11.57 1.193 -0.0778 12.46 1.196 -0.0823 13.34 1.200 -0.0864 14.68 1.186 -0.0946 15.61 1.196 -0.0997 16.53 1.196 -0.1042 17.51 1.210 -0.1120 18.46 1.218 -0.1167 19.46 1.237 -0.1245 17.69 1.216 -0.1129 16.79 1.200 -0.1052 15.50 1.192 -0.1006 14.66 1.187 -0.0951 13.46 1.183 -0.0894 12.63 1.186 -0.0863 11.81 1.191 -0.0804 10.69 1.189 -0.0756 9.49 1.168 -0.0742 8.66 1.137 -0.0779 7.80 1.087 -0.0814 6.54 1.003 -0.0862 5.64 0.942 -0.0902 4.72 0.871 -0.0927 3.41 0.762 -0.0948 2.48 0.676 -0.0955 1.58 0.589 -0.0965 0.28 0.458 -0.0969 -0.62 0.364 -0.0978 -1.54 0.267 -0.0981 -2.48 0.169 -0.0989 -3.80 0.036 -0.0986 -4.75 -0.049 -0.0996 -5.74 -0.129 -0.1002 Tabulated from data in file PG01745.DAT & reduced using program Q06.01L Average Reynolds #: 301700 Number of angles of attack: 49 alpha / Cl / Cm -5.26 -0.116 -0.0936 -3.91 0.017 -0.0949 -2.99 0.109 -0.0952 -1.59 0.256 -0.0945 -0.62 0.358 -0.0944 0.37 0.466 -0.0950 1.32 0.569 -0.0950 2.35 0.670 -0.0938 3.41 0.765 -0.0920 4.41 0.854 -0.0900 5.37 0.936 -0.0879 6.41 1.018 -0.0851 7.43 1.087 -0.0813 8.44 1.135 -0.0760 9.43 1.164 -0.0727 10.36 1.177 -0.0740 11.66 1.193 -0.0841 12.57 1.192 -0.0909 13.50 1.183 -0.0954 14.42 1.180 -0.0992 15.76 1.191 -0.1060 16.29 1.184 -0.1083 17.70 1.203 -0.1133 18.57 1.228 -0.1221 19.40 1.233 -0.1268 17.39 1.207 -0.1162 16.34 1.191 -0.1097 15.36 1.185 -0.1054 14.80 1.189 -0.1028 13.41 1.192 -0.0959 12.50 1.196 -0.0920 11.59 1.191 -0.0842 10.70 1.185 -0.0779 9.52 1.168 -0.0735 8.61 1.141 -0.0762 7.65 1.098 -0.0813 6.67 1.035 -0.0849 5.66 0.956 -0.0878 4.61 0.869 -0.0902 3.56 0.778 -0.0921 2.49 0.684 -0.0939 1.42 0.582 -0.0951 0.41 0.477 -0.0952 -0.54 0.366 -0.0946 -1.50 0.265 -0.0947 -2.50 0.164 -0.0950 -3.50 0.060 -0.0947 -5.01 -0.092 -0.0934 -5.57 -0.143 -0.0938 Tabulated from data in file PG01747.DAT & reduced using program Q06.01L Average Reynolds #: 402300 Number of angles of attack: 49 alpha / Cl / Cm -5.23 -0.122 -0.0931 -3.65 0.038 -0.0943 -2.55 0.153 -0.0948 -1.88 0.222 -0.0947 -0.80 0.346 -0.0950 0.35 0.468 -0.0945 1.51 0.584 -0.0932 2.25 0.656 -0.0922 3.52 0.776 -0.0905 4.24 0.842 -0.0895 5.61 0.957 -0.0868 6.42 1.018 -0.0842 7.83 1.105 -0.0787 8.69 1.137 -0.0747 9.51 1.157 -0.0724 10.48 1.178 -0.0788 11.37 1.183 -0.0864 12.66 1.178 -0.0936 13.55 1.184 -0.0965 14.39 1.179 -0.1011 15.58 1.186 -0.1085 16.39 1.186 -0.1111 17.57 1.205 -0.1199 18.35 1.212 -0.1229 19.39 1.213 -0.1296 17.59 1.198 -0.1194 16.61 1.189 -0.1133 15.67 1.182 -0.1083 14.69 1.172 -0.1042 13.29 1.176 -0.0968 12.70 1.186 -0.0954 11.21 1.185 -0.0851 10.70 1.173 -0.0804 9.67 1.159 -0.0735 8.64 1.135 -0.0750 7.60 1.092 -0.0790 6.43 1.016 -0.0837 5.26 0.927 -0.0872 4.61 0.872 -0.0886 3.51 0.774 -0.0906 2.48 0.676 -0.0920 1.46 0.578 -0.0935 0.45 0.477 -0.0947 -0.50 0.379 -0.0950 -1.78 0.237 -0.0949 -2.65 0.144 -0.0949 -3.54 0.051 -0.0946 -4.82 -0.080 -0.0938 -5.71 -0.170 -0.0926 Tabulated from data in file PG01749.DAT & reduced using program Q06.01L File SD7062BT.LFT created on 10-24-1997 at 19:34:42 using program FORMAT :::::::::::::: SD7080.LFT :::::::::::::: Airfoil: SD7080 Builder: P. Illick Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 59972 Number of angles of attack: 49 alpha / Cl / Cm -5.94 -0.382 -0.0474 -5.03 -0.336 -0.0449 -3.91 -0.269 -0.0397 -2.96 -0.209 -0.0338 -1.91 -0.129 -0.0292 -0.90 -0.036 -0.0244 0.20 0.091 -0.0249 1.20 0.276 -0.0450 2.22 0.416 -0.0519 3.33 0.530 -0.0496 4.21 0.604 -0.0498 5.54 0.693 -0.0452 6.21 0.777 -0.0414 7.44 0.867 -0.0357 8.38 0.953 -0.0316 9.36 1.015 -0.0232 10.41 1.061 -0.0173 11.36 1.080 -0.0134 12.48 1.107 -0.0095 13.41 1.113 -0.0305 14.28 1.144 -0.0921 15.34 0.988 -0.1088 16.39 1.012 -0.1269 17.38 1.006 -0.1283 18.30 1.007 -0.1227 17.53 0.986 -0.1456 16.53 1.028 -0.1339 15.38 0.985 -0.1332 14.63 1.039 -0.1128 13.61 1.035 -0.0981 12.75 1.118 -0.0202 11.58 1.109 -0.0204 10.73 1.088 -0.0233 9.72 1.057 -0.0282 8.69 1.005 -0.0353 7.68 0.945 -0.0408 6.66 0.850 -0.0467 5.60 0.758 -0.0516 4.50 0.663 -0.0551 3.54 0.587 -0.0664 2.53 0.487 -0.0778 1.52 0.358 -0.0681 0.51 0.196 -0.0588 -0.68 0.028 -0.0410 -1.55 -0.044 -0.0347 -2.60 -0.128 -0.0330 -3.60 -0.191 -0.0367 -4.66 -0.260 -0.0405 -5.71 -0.325 -0.0444 Tabulated from data in file cl02584.dat & reduced using program C06.01 Average Reynolds #: 100018 Number of angles of attack: 59 alpha / Cl / Cm -9.02 -0.599 0.0456 -7.99 -0.554 0.0157 -6.90 -0.501 -0.0241 -5.90 -0.432 -0.0437 -4.90 -0.363 -0.0400 -3.89 -0.269 -0.0372 -2.90 -0.164 -0.0377 -1.97 -0.063 -0.0391 -0.75 0.104 -0.0502 0.22 0.238 -0.0584 1.48 0.378 -0.0573 2.14 0.436 -0.0533 3.32 0.529 -0.0470 4.28 0.615 -0.0442 5.37 0.708 -0.0394 6.50 0.808 -0.0356 7.35 0.881 -0.0332 8.26 0.964 -0.0309 9.33 1.016 -0.0226 10.34 1.049 -0.0162 11.34 1.076 -0.0114 12.32 1.086 -0.0086 13.34 1.086 -0.0137 14.33 0.980 -0.1087 15.29 0.918 -0.1266 16.28 0.949 -0.1251 17.36 0.947 -0.1321 18.31 0.944 -0.1293 19.39 0.983 -0.1379 20.40 0.985 -0.1416 19.46 0.945 -0.1445 18.42 0.903 -0.1413 17.42 0.969 -0.1353 16.48 0.935 -0.1281 15.55 0.924 -0.1306 14.53 0.943 -0.1252 13.46 1.144 -0.0883 12.73 1.100 -0.0148 11.69 1.099 -0.0158 10.77 1.076 -0.0197 9.70 1.043 -0.0252 8.73 1.015 -0.0337 7.69 0.948 -0.0377 6.67 0.855 -0.0400 5.64 0.768 -0.0434 4.62 0.681 -0.0469 3.57 0.587 -0.0524 2.37 0.479 -0.0601 1.49 0.401 -0.0668 0.39 0.280 -0.0671 -0.64 0.139 -0.0597 -1.58 -0.002 -0.0499 -2.56 -0.113 -0.0464 -3.71 -0.236 -0.0425 -4.66 -0.324 -0.0416 -5.72 -0.403 -0.0455 -6.67 -0.476 -0.0417 -7.67 -0.551 0.0019 -8.63 -0.584 0.0272 Tabulated from data in file ag02586.dat & reduced using program C06.01 Average Reynolds #: 150082 Number of angles of attack: 59 alpha / Cl / Cm -9.04 -0.578 0.0492 -8.02 -0.542 0.0207 -6.96 -0.491 -0.0205 -5.96 -0.410 -0.0435 -4.87 -0.302 -0.0465 -3.91 -0.193 -0.0483 -2.75 -0.064 -0.0533 -1.75 0.044 -0.0548 -0.78 0.164 -0.0594 0.29 0.258 -0.0547 1.18 0.339 -0.0498 2.20 0.442 -0.0465 3.28 0.554 -0.0451 4.34 0.656 -0.0422 5.33 0.738 -0.0389 6.28 0.826 -0.0362 7.26 0.913 -0.0336 8.25 0.983 -0.0292 9.42 1.025 -0.0203 10.20 1.056 -0.0155 11.46 1.080 -0.0092 12.31 1.083 -0.0083 13.34 1.081 -0.0141 14.37 1.041 -0.1086 15.32 0.938 -0.1324 16.31 0.926 -0.1319 17.31 0.933 -0.1266 18.36 0.943 -0.1364 19.26 0.911 -0.1347 20.51 0.959 -0.1467 19.53 0.941 -0.1424 18.61 0.954 -0.1397 17.58 0.924 -0.1344 16.60 0.909 -0.1359 15.65 0.951 -0.1338 14.69 1.049 -0.1314 13.71 1.055 -0.0806 12.71 1.085 -0.0154 11.69 1.087 -0.0141 10.72 1.076 -0.0177 9.70 1.045 -0.0239 8.74 1.007 -0.0309 7.66 0.954 -0.0380 6.66 0.858 -0.0396 5.62 0.770 -0.0426 4.56 0.674 -0.0453 3.60 0.591 -0.0486 2.53 0.485 -0.0522 1.45 0.370 -0.0538 0.48 0.279 -0.0587 -0.63 0.181 -0.0627 -1.57 0.059 -0.0604 -2.60 -0.045 -0.0605 -3.70 -0.163 -0.0552 -4.69 -0.274 -0.0519 -5.74 -0.380 -0.0493 -6.64 -0.468 -0.0378 -7.64 -0.535 -0.0016 -8.61 -0.573 0.0305 Tabulated from data in file ag02589.dat & reduced using program C06.01 Average Reynolds #: 199979 Number of angles of attack: 59 alpha / Cl / Cm -9.15 -0.597 0.0511 -8.00 -0.559 0.0166 -6.92 -0.487 -0.0243 -5.92 -0.377 -0.0515 -4.88 -0.256 -0.0551 -3.55 -0.110 -0.0582 -2.86 -0.038 -0.0597 -1.72 0.057 -0.0560 -0.70 0.155 -0.0527 0.18 0.245 -0.0511 1.29 0.364 -0.0503 2.21 0.459 -0.0487 3.29 0.570 -0.0460 4.34 0.672 -0.0432 5.34 0.771 -0.0410 6.21 0.854 -0.0392 7.38 0.955 -0.0365 8.34 1.012 -0.0307 9.30 1.052 -0.0235 10.26 1.085 -0.0171 11.31 1.103 -0.0120 12.31 1.110 -0.0117 13.19 1.104 -0.0211 14.26 1.062 -0.0951 15.26 0.988 -0.1307 16.27 0.945 -0.1351 17.30 0.962 -0.1361 18.24 0.935 -0.1329 19.21 0.957 -0.1411 20.26 1.005 -0.1406 19.38 0.965 -0.1518 18.39 0.975 -0.1371 17.43 0.971 -0.1385 16.46 0.966 -0.1346 15.36 0.979 -0.1383 14.49 1.045 -0.1189 13.62 1.123 -0.0978 12.76 1.102 -0.0177 11.73 1.110 -0.0129 10.71 1.098 -0.0166 9.71 1.067 -0.0222 8.70 1.026 -0.0295 7.69 0.980 -0.0363 6.61 0.885 -0.0401 5.66 0.798 -0.0425 4.56 0.697 -0.0450 3.43 0.586 -0.0474 2.50 0.492 -0.0501 1.50 0.387 -0.0515 0.45 0.278 -0.0527 -0.60 0.174 -0.0539 -1.72 0.058 -0.0572 -2.58 -0.013 -0.0610 -3.60 -0.114 -0.0596 -4.63 -0.226 -0.0573 -5.62 -0.338 -0.0537 -6.62 -0.453 -0.0398 -7.65 -0.552 0.0015 -8.66 -0.582 0.0377 Tabulated from data in file ag02591.dat & reduced using program C06.01 Average Reynolds #: 300010 Number of angles of attack: 45 alpha / Cl / Cm -9.19 -0.627 0.0516 -7.87 -0.574 0.0007 -7.25 -0.523 -0.0249 -6.12 -0.384 -0.0584 -5.14 -0.271 -0.0598 -4.15 -0.174 -0.0592 -3.10 -0.075 -0.0569 -1.82 0.033 -0.0529 -0.86 0.123 -0.0496 0.16 0.254 -0.0534 1.33 0.376 -0.0514 2.39 0.486 -0.0493 3.29 0.578 -0.0476 4.25 0.671 -0.0452 5.30 0.775 -0.0434 6.24 0.867 -0.0414 7.35 0.962 -0.0376 8.26 1.016 -0.0320 9.49 1.071 -0.0237 10.25 1.102 -0.0184 11.36 1.126 -0.0140 12.27 1.128 -0.0136 13.20 1.150 -0.0181 12.73 1.129 -0.0177 11.76 1.134 -0.0155 10.69 1.117 -0.0173 9.69 1.081 -0.0218 8.69 1.035 -0.0286 7.66 0.983 -0.0347 6.46 0.885 -0.0400 5.66 0.808 -0.0418 4.66 0.706 -0.0441 3.54 0.596 -0.0472 2.55 0.496 -0.0496 1.38 0.379 -0.0521 0.35 0.272 -0.0538 -0.63 0.158 -0.0519 -1.66 0.047 -0.0532 -2.66 -0.040 -0.0562 -3.77 -0.140 -0.0593 -4.81 -0.239 -0.0607 -5.74 -0.338 -0.0605 -6.83 -0.468 -0.0463 -7.59 -0.552 -0.0122 -8.61 -0.611 0.0331 Tabulated from data in file ag02593.dat & reduced using program C06.01 File sd7080.lft created using program C06.01 on Mon Feb 02 15:11:35 1998 :::::::::::::: SG6040.LFT :::::::::::::: Airfoil: SG6040 Builder: M. Allen Comment: clean Number of Reynolds #'s: 6 Average Reynolds #: 100032 Number of angles of attack: 59 alpha / Cl / Cm -8.59 -0.628 -0.0543 -7.45 -0.586 -0.0503 -6.68 -0.530 -0.0520 -5.72 -0.445 -0.0572 -4.75 -0.324 -0.0689 -3.71 -0.190 -0.0758 -2.67 -0.142 -0.0618 -1.64 -0.046 -0.0600 -0.58 0.060 -0.0590 0.97 0.170 -0.0590 1.18 0.188 -0.0578 2.31 0.293 -0.0619 3.47 0.385 -0.0675 4.24 0.438 -0.0725 5.27 0.602 -0.0787 6.53 0.900 -0.0784 7.42 1.001 -0.0791 8.39 1.085 -0.0781 9.48 1.168 -0.0768 10.43 1.232 -0.0738 11.42 1.258 -0.0620 12.61 1.273 -0.0522 13.40 1.268 -0.0465 14.55 1.293 -0.0425 15.47 1.282 -0.0423 16.28 0.939 -0.1310 17.33 0.898 -0.1447 18.35 0.967 -0.1449 19.27 0.925 -0.1428 20.37 0.950 -0.1546 19.65 1.015 -0.1637 18.62 0.975 -0.1592 17.64 0.947 -0.1473 16.57 0.894 -0.1360 15.65 0.906 -0.1306 14.70 0.931 -0.1354 13.92 1.267 -0.0551 12.90 1.288 -0.0534 11.86 1.261 -0.0596 10.67 1.254 -0.0724 9.83 1.223 -0.0781 8.78 1.145 -0.0780 7.83 1.067 -0.0790 6.78 0.964 -0.0791 5.74 0.821 -0.0773 4.60 0.485 -0.0734 3.63 0.429 -0.0679 2.65 0.335 -0.0611 1.59 0.236 -0.0554 0.59 0.197 -0.0576 -0.51 0.077 -0.0541 -1.55 -0.031 -0.0552 -2.45 -0.123 -0.0562 -3.64 -0.169 -0.0708 -4.54 -0.282 -0.0645 -5.56 -0.402 -0.0496 -6.55 -0.500 -0.0413 -7.63 -0.582 -0.0380 -8.61 -0.618 -0.0417 Tabulated from data in file pg02398.dat & reduced using program C06.01 Average Reynolds #: 149935 Number of angles of attack: 59 alpha / Cl / Cm -8.86 -0.657 -0.0461 -7.81 -0.594 -0.0467 -6.69 -0.481 -0.0573 -5.84 -0.362 -0.0708 -4.77 -0.220 -0.0843 -3.66 -0.080 -0.0882 -2.82 0.013 -0.0874 -1.74 0.128 -0.0821 -0.69 0.222 -0.0777 0.54 0.327 -0.0739 1.82 0.439 -0.0727 2.35 0.493 -0.0724 3.73 0.625 -0.0718 4.40 0.694 -0.0712 5.43 0.805 -0.0701 6.44 0.927 -0.0770 7.47 1.037 -0.0788 8.50 1.131 -0.0777 9.50 1.207 -0.0748 10.65 1.261 -0.0655 11.57 1.261 -0.0557 12.48 1.285 -0.0500 13.75 1.312 -0.0440 14.52 1.319 -0.0420 15.65 1.333 -0.0423 16.51 1.318 -0.0450 17.26 0.902 -0.1404 18.56 0.917 -0.1562 19.53 0.974 -0.1603 20.48 0.972 -0.1658 19.51 0.889 -0.1702 18.34 0.918 -0.1612 17.49 0.909 -0.1519 16.31 0.888 -0.1524 15.40 0.909 -0.1450 14.78 1.327 -0.0477 13.80 1.315 -0.0473 12.79 1.301 -0.0522 11.82 1.274 -0.0583 10.78 1.269 -0.0680 9.71 1.234 -0.0778 8.65 1.147 -0.0810 7.66 1.059 -0.0820 6.71 0.966 -0.0807 5.69 0.839 -0.0736 4.50 0.722 -0.0732 3.63 0.631 -0.0738 2.61 0.522 -0.0741 1.60 0.426 -0.0737 0.35 0.317 -0.0759 -0.50 0.249 -0.0777 -1.51 0.156 -0.0822 -2.51 0.057 -0.0865 -3.77 -0.088 -0.0881 -4.65 -0.198 -0.0844 -5.91 -0.368 -0.0685 -6.72 -0.481 -0.0558 -7.82 -0.594 -0.0442 -8.92 -0.653 -0.0448 Tabulated from data in file cf02401.dat & reduced using program C06.01 Average Reynolds #: 199981 Number of angles of attack: 59 alpha / Cl / Cm -8.80 -0.665 -0.0503 -7.79 -0.535 -0.0636 -6.67 -0.377 -0.0810 -5.76 -0.262 -0.0900 -4.67 -0.142 -0.0930 -3.54 -0.035 -0.0900 -2.73 0.043 -0.0871 -1.71 0.141 -0.0844 -0.54 0.258 -0.0820 0.32 0.349 -0.0820 1.28 0.453 -0.0818 2.28 0.551 -0.0817 3.40 0.665 -0.0818 4.34 0.753 -0.0809 5.40 0.854 -0.0787 6.37 0.939 -0.0757 7.34 1.056 -0.0794 8.41 1.159 -0.0786 9.35 1.231 -0.0742 10.56 1.273 -0.0636 11.43 1.280 -0.0544 12.65 1.300 -0.0467 13.78 1.325 -0.0427 14.42 1.333 -0.0415 15.58 1.353 -0.0433 16.45 1.353 -0.0465 17.44 1.338 -0.0529 18.50 0.876 -0.1512 19.82 0.939 -0.1708 20.44 1.009 -0.1728 19.32 0.918 -0.1589 18.43 0.889 -0.1553 17.45 0.883 -0.1418 16.43 0.889 -0.1415 15.56 0.865 -0.1398 14.80 1.345 -0.0424 13.89 1.330 -0.0426 12.71 1.306 -0.0457 11.90 1.288 -0.0504 10.84 1.273 -0.0587 9.87 1.255 -0.0687 8.77 1.185 -0.0752 7.80 1.096 -0.0763 6.70 0.976 -0.0740 5.75 0.881 -0.0740 4.63 0.778 -0.0772 3.59 0.683 -0.0786 2.53 0.579 -0.0788 1.60 0.482 -0.0785 0.42 0.358 -0.0791 -0.54 0.259 -0.0796 -1.63 0.148 -0.0817 -2.71 0.041 -0.0850 -3.61 -0.045 -0.0879 -4.68 -0.147 -0.0905 -5.73 -0.260 -0.0878 -6.76 -0.389 -0.0766 -7.72 -0.524 -0.0620 -8.67 -0.644 -0.0482 Tabulated from data in file cf02404.dat & reduced using program C06.01 Average Reynolds #: 300055 Number of angles of attack: 59 alpha / Cl / Cm -8.96 -0.608 -0.0729 -8.06 -0.480 -0.0856 -7.10 -0.366 -0.0938 -5.92 -0.264 -0.0937 -4.95 -0.177 -0.0925 -3.94 -0.082 -0.0910 -2.94 0.020 -0.0904 -1.72 0.149 -0.0896 -0.79 0.249 -0.0894 0.23 0.358 -0.0892 1.39 0.484 -0.0888 2.42 0.597 -0.0888 3.35 0.694 -0.0888 4.64 0.824 -0.0880 5.49 0.913 -0.0867 6.51 1.013 -0.0838 7.69 1.118 -0.0804 8.60 1.191 -0.0775 9.59 1.246 -0.0701 10.48 1.275 -0.0616 11.45 1.286 -0.0525 12.64 1.312 -0.0456 13.43 1.326 -0.0438 14.43 1.345 -0.0441 15.55 1.371 -0.0463 16.48 1.382 -0.0487 17.47 1.386 -0.0537 18.47 1.384 -0.0580 19.52 1.380 -0.0695 20.07 0.989 -0.1857 19.72 0.939 -0.1789 18.70 0.904 -0.1636 17.42 0.864 -0.1529 16.50 0.884 -0.1472 16.16 1.380 -0.0482 14.77 1.356 -0.0438 13.85 1.340 -0.0427 12.87 1.321 -0.0441 11.84 1.300 -0.0488 10.82 1.287 -0.0562 9.83 1.264 -0.0655 8.79 1.209 -0.0744 7.71 1.124 -0.0778 6.61 1.030 -0.0821 5.68 0.939 -0.0851 4.47 0.817 -0.0873 2.82 0.643 -0.0882 2.58 0.615 -0.0882 1.35 0.485 -0.0888 0.33 0.373 -0.0884 -0.58 0.272 -0.0882 -1.59 0.165 -0.0886 -2.67 0.050 -0.0891 -3.80 -0.065 -0.0898 -4.69 -0.151 -0.0903 -5.76 -0.246 -0.0919 -6.55 -0.311 -0.0933 -7.62 -0.420 -0.0898 -8.68 -0.568 -0.0768 Tabulated from data in file cf02407.dat & reduced using program C06.01 Average Reynolds #: 399673 Number of angles of attack: 59 alpha / Cl / Cm -9.02 -0.570 -0.0869 -8.03 -0.453 -0.0948 -7.06 -0.369 -0.0944 -5.89 -0.271 -0.0927 -5.03 -0.186 -0.0918 -3.99 -0.087 -0.0921 -2.99 0.018 -0.0918 -1.93 0.134 -0.0913 -0.91 0.247 -0.0909 0.14 0.363 -0.0906 1.20 0.484 -0.0909 2.25 0.596 -0.0915 3.24 0.702 -0.0919 4.48 0.837 -0.0915 5.25 0.918 -0.0907 6.26 1.020 -0.0891 7.57 1.132 -0.0831 8.52 1.198 -0.0773 9.78 1.256 -0.0666 10.59 1.279 -0.0595 11.73 1.304 -0.0511 12.70 1.325 -0.0477 13.44 1.341 -0.0473 14.44 1.365 -0.0490 15.49 1.384 -0.0508 16.65 1.394 -0.0564 17.65 1.416 -0.0582 18.64 1.400 -0.0637 19.60 1.404 -0.0716 20.73 1.401 -0.0799 19.81 1.408 -0.0740 18.89 1.402 -0.0664 17.79 1.400 -0.0600 16.83 1.384 -0.0552 15.88 1.392 -0.0514 14.87 1.373 -0.0478 13.92 1.356 -0.0456 12.87 1.335 -0.0439 11.88 1.313 -0.0466 10.70 1.285 -0.0538 9.79 1.261 -0.0620 8.71 1.213 -0.0715 7.75 1.149 -0.0777 6.27 1.023 -0.0846 5.58 0.956 -0.0863 4.56 0.846 -0.0877 3.60 0.747 -0.0892 2.61 0.639 -0.0898 1.63 0.534 -0.0906 0.59 0.414 -0.0901 -0.48 0.301 -0.0908 -1.67 0.166 -0.0908 -2.56 0.064 -0.0906 -3.49 -0.036 -0.0901 -4.55 -0.144 -0.0900 -5.54 -0.237 -0.0900 -6.58 -0.328 -0.0908 -7.63 -0.412 -0.0924 -8.63 -0.519 -0.0891 Tabulated from data in file cf02409.dat & reduced using program C06.01 Average Reynolds #: 499595 Number of angles of attack: 53 alpha / Cl / Cm -6.01 -0.291 -0.0918 -4.99 -0.189 -0.0917 -4.00 -0.089 -0.0919 -2.93 0.030 -0.0907 -1.95 0.143 -0.0903 -0.90 0.262 -0.0906 0.11 0.376 -0.0910 1.13 0.495 -0.0908 2.17 0.610 -0.0908 3.24 0.727 -0.0902 4.27 0.841 -0.0896 5.28 0.946 -0.0884 6.59 1.073 -0.0850 7.38 1.142 -0.0816 8.61 1.214 -0.0712 10.01 1.270 -0.0598 11.02 1.301 -0.0530 11.77 1.311 -0.0484 12.84 1.339 -0.0476 13.81 1.363 -0.0494 14.65 1.374 -0.0511 15.84 1.387 -0.0545 16.89 1.391 -0.0586 18.31 1.404 -0.0651 18.31 1.398 -0.0658 19.71 1.406 -0.0727 20.73 1.422 -0.0809 19.62 1.403 -0.0736 18.70 1.409 -0.0667 17.88 1.387 -0.0620 16.84 1.396 -0.0571 15.84 1.395 -0.0532 14.81 1.380 -0.0491 13.82 1.363 -0.0467 12.87 1.340 -0.0425 11.72 1.316 -0.0439 10.46 1.285 -0.0512 9.80 1.269 -0.0563 8.46 1.206 -0.0688 7.23 1.130 -0.0787 6.44 1.064 -0.0826 5.49 0.972 -0.0856 4.57 0.874 -0.0869 3.70 0.784 -0.0879 2.69 0.672 -0.0873 1.60 0.554 -0.0893 0.64 0.442 -0.0894 -0.44 0.325 -0.0896 -1.54 0.194 -0.0894 -2.44 0.087 -0.0897 -3.54 -0.039 -0.0893 -4.55 -0.147 -0.0890 -5.63 -0.257 -0.0884 Tabulated from data in file cf02412.dat & reduced using program C06.01 File sg6040.lft created using program C06.01 on Mon Feb 02 15:11:35 1998 :::::::::::::: SG6040T.LFT :::::::::::::: Airfoil: SG6040 Builder: M. Allen Comment: Zigzag trip Type C (h = 0.023") @ 2% u.s. & 5% l.s. Number of Reynolds #'s: 6 Average Reynolds #: 100006 Number of angles of attack: 59 alpha / Cl / Cm -8.99 -0.635 -0.0479 -7.96 -0.624 -0.0414 -6.90 -0.569 -0.0398 -5.83 -0.478 -0.0449 -4.71 -0.326 -0.0557 -3.59 -0.211 -0.0626 -2.82 -0.158 -0.0641 -1.84 -0.047 -0.0730 -0.70 0.078 -0.0792 0.63 0.206 -0.0817 1.61 0.322 -0.0782 2.30 0.438 -0.0659 3.53 0.549 -0.0505 4.38 0.620 -0.0484 5.56 0.707 -0.0520 6.44 0.768 -0.0516 7.45 0.823 -0.0489 8.57 0.883 -0.0447 9.32 0.931 -0.0425 10.71 0.971 -0.0378 11.46 0.990 -0.0368 12.46 1.020 -0.0372 13.49 1.045 -0.0385 14.57 1.054 -0.0406 15.71 1.075 -0.0443 16.40 1.080 -0.0487 17.25 0.864 -0.1339 18.75 0.891 -0.1550 19.28 0.930 -0.1580 20.50 0.976 -0.1663 19.28 0.934 -0.1716 18.47 0.895 -0.1583 17.56 0.947 -0.1464 16.50 0.961 -0.1395 15.62 0.849 -0.1082 14.86 1.069 -0.0524 13.85 1.048 -0.0441 12.83 1.031 -0.0416 11.81 1.013 -0.0405 10.76 0.987 -0.0418 9.79 0.964 -0.0447 8.77 0.918 -0.0483 7.75 0.870 -0.0520 6.56 0.797 -0.0548 5.73 0.739 -0.0558 4.63 0.658 -0.0530 3.72 0.593 -0.0539 2.55 0.498 -0.0655 1.52 0.334 -0.0834 0.48 0.217 -0.0839 -0.47 0.134 -0.0820 -1.51 0.022 -0.0769 -2.59 -0.108 -0.0676 -3.53 -0.203 -0.0619 -4.69 -0.317 -0.0551 -5.53 -0.426 -0.0457 -6.55 -0.524 -0.0401 -7.68 -0.603 -0.0370 -8.68 -0.633 -0.0425 Tabulated from data in file pg02507.dat & reduced using program C06.01 Average Reynolds #: 150010 Number of angles of attack: 57 alpha / Cl / Cm -7.82 -0.477 -0.0486 -6.77 -0.424 -0.0559 -5.83 -0.335 -0.0696 -4.75 -0.202 -0.0815 -3.70 -0.071 -0.0899 -2.67 0.036 -0.0931 -1.64 0.128 -0.0927 -0.66 0.228 -0.0916 0.77 0.368 -0.0851 1.22 0.412 -0.0834 2.27 0.499 -0.0792 3.37 0.578 -0.0721 4.36 0.635 -0.0642 5.84 0.723 -0.0526 6.32 0.763 -0.0522 7.56 0.851 -0.0500 8.27 0.888 -0.0475 9.48 0.936 -0.0429 10.37 0.961 -0.0400 11.48 0.992 -0.0399 12.49 1.017 -0.0423 13.70 1.027 -0.0457 14.44 1.037 -0.0498 15.48 1.052 -0.0558 16.81 1.076 -0.0614 17.48 1.087 -0.0661 18.41 0.894 -0.1521 19.53 0.879 -0.1643 20.55 0.935 -0.1719 19.48 0.909 -0.1726 18.38 0.905 -0.1489 17.52 0.919 -0.1417 16.55 0.876 -0.1311 15.67 1.073 -0.0617 14.81 1.060 -0.0552 13.73 1.046 -0.0506 12.83 1.020 -0.0485 11.79 1.007 -0.0455 10.75 0.981 -0.0435 9.68 0.953 -0.0457 8.80 0.915 -0.0495 7.73 0.864 -0.0525 6.72 0.806 -0.0544 5.76 0.734 -0.0549 4.71 0.665 -0.0617 3.55 0.596 -0.0719 2.47 0.523 -0.0781 1.59 0.450 -0.0813 0.39 0.340 -0.0866 -0.58 0.249 -0.0911 -1.61 0.148 -0.0926 -2.65 0.033 -0.0926 -3.64 -0.071 -0.0893 -4.76 -0.212 -0.0801 -5.70 -0.341 -0.0696 -6.79 -0.457 -0.0545 -7.58 -0.485 -0.0467 Tabulated from data in file pg02504.dat & reduced using program C06.01 Average Reynolds #: 199946 Number of angles of attack: 59 alpha / Cl / Cm -8.71 -0.667 -0.0522 -7.75 -0.560 -0.0619 -6.72 -0.398 -0.0791 -5.63 -0.241 -0.0902 -4.56 -0.120 -0.0942 -3.48 -0.016 -0.0931 -2.44 0.082 -0.0910 -1.70 0.155 -0.0907 -0.52 0.267 -0.0865 0.36 0.349 -0.0840 1.48 0.446 -0.0800 2.50 0.531 -0.0758 3.42 0.602 -0.0720 4.38 0.677 -0.0688 5.62 0.764 -0.0627 6.92 0.839 -0.0532 7.41 0.871 -0.0516 8.47 0.925 -0.0474 9.48 0.966 -0.0434 10.40 0.994 -0.0418 11.45 1.022 -0.0422 12.48 1.041 -0.0452 13.66 1.061 -0.0502 14.56 1.078 -0.0546 15.71 1.080 -0.0605 16.45 1.085 -0.0664 17.48 1.086 -0.0733 18.34 0.905 -0.1518 19.48 0.890 -0.1531 20.54 0.929 -0.1767 19.42 0.934 -0.1621 18.13 0.900 -0.1612 17.30 0.920 -0.1471 16.53 1.095 -0.0701 15.78 1.100 -0.0632 14.61 1.073 -0.0576 13.80 1.054 -0.0545 12.76 1.062 -0.0483 11.82 1.032 -0.0454 10.74 1.006 -0.0427 9.83 0.981 -0.0433 8.62 0.935 -0.0472 7.51 0.879 -0.0514 6.68 0.832 -0.0552 5.69 0.774 -0.0629 4.36 0.675 -0.0693 3.64 0.617 -0.0714 2.36 0.518 -0.0755 1.48 0.446 -0.0791 0.50 0.361 -0.0824 -0.56 0.266 -0.0858 -1.63 0.165 -0.0893 -2.69 0.063 -0.0902 -3.65 -0.025 -0.0919 -4.78 -0.141 -0.0927 -5.68 -0.243 -0.0885 -6.72 -0.384 -0.0779 -7.78 -0.555 -0.0602 -9.06 -0.686 -0.0486 Tabulated from data in file pg02508.dat & reduced using program C06.01 Average Reynolds #: 299965 Number of angles of attack: 59 alpha / Cl / Cm -9.13 -0.665 -0.0672 -8.00 -0.492 -0.0849 -7.09 -0.370 -0.0942 -5.89 -0.251 -0.0953 -4.87 -0.156 -0.0927 -4.03 -0.076 -0.0907 -2.86 0.036 -0.0883 -1.76 0.131 -0.0839 -0.73 0.233 -0.0830 0.31 0.337 -0.0805 1.53 0.446 -0.0765 2.56 0.539 -0.0738 3.66 0.638 -0.0709 4.67 0.722 -0.0680 5.78 0.814 -0.0637 6.52 0.864 -0.0603 7.63 0.924 -0.0538 8.57 0.963 -0.0479 9.53 0.999 -0.0439 10.54 1.030 -0.0425 11.46 1.059 -0.0455 12.56 1.075 -0.0492 13.62 1.100 -0.0545 14.51 1.106 -0.0599 15.58 1.095 -0.0672 16.58 1.112 -0.0765 17.75 1.105 -0.0858 18.37 1.006 -0.1512 19.16 1.025 -0.1621 20.05 0.996 -0.1714 19.68 0.973 -0.1671 18.71 1.003 -0.1551 17.69 1.073 -0.1478 16.90 1.109 -0.0778 15.73 1.114 -0.0710 14.79 1.105 -0.0630 13.84 1.104 -0.0570 12.73 1.084 -0.0514 11.81 1.065 -0.0472 10.76 1.042 -0.0433 9.56 1.004 -0.0441 8.76 0.975 -0.0471 7.78 0.936 -0.0530 6.61 0.873 -0.0594 5.41 0.787 -0.0648 4.42 0.707 -0.0684 3.26 0.606 -0.0722 2.45 0.537 -0.0745 1.18 0.427 -0.0782 0.30 0.344 -0.0813 -0.69 0.237 -0.0830 -1.87 0.127 -0.0836 -2.63 0.063 -0.0869 -3.71 -0.041 -0.0896 -4.72 -0.138 -0.0913 -5.63 -0.221 -0.0932 -6.84 -0.339 -0.0943 -7.65 -0.438 -0.0886 -8.76 -0.602 -0.0734 Tabulated from data in file pg02509.dat & reduced using program C06.01 Average Reynolds #: 400026 Number of angles of attack: 49 alpha / Cl / Cm -7.08 -0.373 -0.0945 -5.98 -0.275 -0.0924 -5.00 -0.179 -0.0906 -3.99 -0.084 -0.0878 -2.91 0.011 -0.0833 -1.97 0.108 -0.0825 -0.93 0.216 -0.0805 0.19 0.319 -0.0770 1.22 0.423 -0.0748 2.24 0.517 -0.0726 3.33 0.617 -0.0698 4.42 0.709 -0.0668 5.52 0.798 -0.0630 6.71 0.880 -0.0580 8.07 0.952 -0.0513 8.53 0.973 -0.0492 9.66 1.016 -0.0456 10.52 1.040 -0.0475 11.65 1.065 -0.0519 12.79 1.095 -0.0555 13.97 1.100 -0.0594 14.71 1.108 -0.0641 15.78 1.124 -0.0695 16.60 1.126 -0.0773 17.43 1.110 -0.0868 16.48 1.114 -0.0779 15.58 1.126 -0.0699 14.65 1.120 -0.0664 13.78 1.104 -0.0613 12.56 1.091 -0.0560 11.65 1.068 -0.0538 10.73 1.046 -0.0514 9.79 1.017 -0.0501 8.48 0.974 -0.0486 7.67 0.935 -0.0521 6.48 0.869 -0.0579 5.54 0.803 -0.0611 4.32 0.706 -0.0652 3.37 0.624 -0.0681 2.38 0.533 -0.0705 1.46 0.445 -0.0726 0.53 0.356 -0.0746 -0.49 0.266 -0.0774 -1.44 0.170 -0.0805 -2.78 0.025 -0.0809 -3.58 -0.044 -0.0837 -4.74 -0.151 -0.0873 -5.60 -0.235 -0.0879 -6.53 -0.318 -0.0897 Tabulated from data in file cf02511.dat & reduced using program C06.01 Average Reynolds #: 499355 Number of angles of attack: 49 alpha / Cl / Cm -7.00 -0.380 -0.0919 -5.92 -0.287 -0.0910 -5.00 -0.192 -0.0895 -3.99 -0.096 -0.0871 -2.98 0.002 -0.0853 -1.92 0.113 -0.0829 -0.91 0.223 -0.0799 0.15 0.324 -0.0765 1.13 0.428 -0.0754 2.17 0.528 -0.0732 3.17 0.620 -0.0710 4.27 0.715 -0.0662 5.29 0.796 -0.0617 6.41 0.873 -0.0569 7.68 0.943 -0.0510 8.77 0.992 -0.0481 10.15 1.037 -0.0466 10.94 1.063 -0.0476 11.91 1.086 -0.0558 12.58 1.095 -0.0592 13.89 1.115 -0.0640 14.53 1.112 -0.0690 15.33 1.123 -0.0745 16.26 1.123 -0.0818 17.25 1.136 -0.0930 16.69 1.126 -0.0880 15.49 1.122 -0.0774 14.48 1.117 -0.0692 13.51 1.111 -0.0640 12.70 1.096 -0.0609 11.65 1.079 -0.0574 10.68 1.052 -0.0547 9.80 1.028 -0.0481 8.82 0.995 -0.0460 7.74 0.952 -0.0504 6.59 0.888 -0.0546 5.15 0.791 -0.0609 4.27 0.720 -0.0643 3.46 0.654 -0.0655 2.67 0.580 -0.0687 1.62 0.481 -0.0729 0.63 0.379 -0.0747 -0.40 0.282 -0.0762 -1.42 0.174 -0.0782 -2.45 0.065 -0.0810 -3.48 -0.045 -0.0824 -4.60 -0.152 -0.0861 -5.53 -0.244 -0.0894 -6.61 -0.351 -0.0895 Tabulated from data in file cf02512.dat & reduced using program C06.01 File sg6040t.lft created using program C06.01 on Mon Feb 02 15:11:35 1998 :::::::::::::: SG6041.LFT :::::::::::::: Airfoil: SG6041 Builder: M. Allen Comment: clean Number of Reynolds #'s: 6 Average Reynolds #: 99924 Number of angles of attack: 59 alpha / Cl / Cm -8.97 -0.523 0.0188 -7.95 -0.518 0.0019 -7.02 -0.485 -0.0334 -6.02 -0.405 -0.0454 -5.01 -0.332 -0.0432 -3.99 -0.238 -0.0424 -2.98 -0.144 -0.0443 -1.94 -0.061 -0.0376 -0.82 0.034 -0.0394 0.20 0.150 -0.0508 1.17 0.303 -0.0667 2.20 0.475 -0.0776 3.23 0.618 -0.0786 4.28 0.721 -0.0712 5.28 0.815 -0.0659 6.32 0.899 -0.0622 7.44 0.969 -0.0557 8.40 1.021 -0.0505 9.37 1.083 -0.0465 10.40 1.130 -0.0410 11.37 1.152 -0.0368 12.31 1.013 -0.1218 13.23 0.924 -0.1355 14.17 0.924 -0.1420 15.36 0.982 -0.1460 16.23 0.936 -0.1470 17.29 0.983 -0.1440 18.31 0.987 -0.1554 19.21 1.006 -0.1545 20.24 1.028 -0.1750 19.64 1.005 -0.1545 18.66 0.987 -0.1658 17.58 0.928 -0.1536 16.47 0.959 -0.1590 15.71 0.954 -0.1516 14.66 0.948 -0.1463 13.59 0.934 -0.1490 12.66 0.977 -0.1391 11.77 1.048 -0.1122 10.87 1.146 -0.0411 9.71 1.099 -0.0462 8.84 1.053 -0.0499 7.83 0.991 -0.0545 6.81 0.926 -0.0591 5.78 0.855 -0.0646 4.74 0.775 -0.0703 3.69 0.675 -0.0800 2.65 0.566 -0.0860 1.65 0.393 -0.0750 0.60 0.215 -0.0583 -0.46 0.065 -0.0428 -1.40 -0.027 -0.0342 -2.45 -0.094 -0.0419 -3.47 -0.186 -0.0406 -4.50 -0.283 -0.0390 -5.58 -0.366 -0.0406 -6.55 -0.437 -0.0384 -7.53 -0.493 -0.0175 -8.53 -0.517 0.0146 Tabulated from data in file ag02330.dat & reduced using program C06.01 Average Reynolds #: 150078 Number of angles of attack: 59 alpha / Cl / Cm -8.77 -0.552 0.0154 -7.68 -0.526 -0.0114 -6.87 -0.493 -0.0310 -5.71 -0.404 -0.0459 -4.72 -0.339 -0.0426 -3.69 -0.240 -0.0441 -2.79 -0.137 -0.0479 -1.13 0.041 -0.0514 -0.71 0.084 -0.0527 0.27 0.251 -0.0689 1.55 0.425 -0.0745 2.32 0.491 -0.0722 3.42 0.580 -0.0667 4.39 0.686 -0.0664 5.48 0.796 -0.0624 6.48 0.878 -0.0584 7.57 0.946 -0.0533 8.46 1.005 -0.0495 9.56 1.079 -0.0445 10.61 1.134 -0.0390 11.56 1.163 -0.0342 12.30 0.986 -0.1277 13.63 0.921 -0.1375 14.73 0.893 -0.1411 15.48 0.910 -0.1418 16.75 0.900 -0.1498 17.49 0.921 -0.1547 18.77 0.938 -0.1507 19.88 0.960 -0.1611 20.45 0.948 -0.1609 19.55 0.960 -0.1659 18.51 0.926 -0.1587 17.42 0.898 -0.1498 16.61 0.918 -0.1538 15.52 0.910 -0.1496 14.49 0.898 -0.1455 13.56 0.935 -0.1417 12.69 0.928 -0.1344 11.85 1.167 -0.0359 10.85 1.151 -0.0381 9.81 1.102 -0.0438 8.89 1.040 -0.0481 7.80 0.971 -0.0524 6.69 0.897 -0.0565 5.78 0.833 -0.0600 4.73 0.742 -0.0642 3.74 0.629 -0.0655 2.51 0.511 -0.0675 1.48 0.422 -0.0707 0.57 0.309 -0.0689 -0.70 0.091 -0.0489 -1.41 0.010 -0.0450 -2.53 -0.089 -0.0455 -3.44 -0.195 -0.0387 -4.63 -0.317 -0.0366 -5.50 -0.386 -0.0382 -6.48 -0.454 -0.0368 -7.53 -0.525 -0.0111 -8.49 -0.537 0.0100 Tabulated from data in file pg02503.dat & reduced using program C06.01 Average Reynolds #: 199973 Number of angles of attack: 59 alpha / Cl / Cm -8.98 -0.547 0.0220 -7.93 -0.542 -0.0046 -7.04 -0.512 -0.0312 -5.99 -0.424 -0.0470 -5.00 -0.338 -0.0456 -3.92 -0.225 -0.0481 -2.92 -0.108 -0.0539 -1.83 0.030 -0.0642 -0.92 0.149 -0.0699 0.14 0.281 -0.0737 1.20 0.402 -0.0740 2.21 0.499 -0.0697 3.20 0.608 -0.0692 4.26 0.720 -0.0668 5.28 0.807 -0.0629 6.29 0.891 -0.0590 7.28 0.969 -0.0546 8.29 1.046 -0.0499 9.41 1.115 -0.0444 10.37 1.166 -0.0392 11.39 1.206 -0.0330 12.42 1.222 -0.0285 13.46 0.929 -0.1427 14.33 0.910 -0.1463 15.36 0.899 -0.1516 16.45 0.940 -0.1474 17.18 0.956 -0.1468 18.27 0.958 -0.1541 19.26 0.958 -0.1584 20.32 1.000 -0.1613 19.76 1.011 -0.1625 18.76 0.992 -0.1600 17.49 0.933 -0.1581 16.44 0.925 -0.1539 15.54 0.928 -0.1495 14.35 0.902 -0.1498 13.57 0.917 -0.1468 12.60 0.953 -0.1413 11.92 1.220 -0.0301 10.80 1.190 -0.0362 9.85 1.143 -0.0418 8.89 1.085 -0.0470 7.85 1.011 -0.0517 6.76 0.925 -0.0568 5.64 0.836 -0.0606 4.68 0.756 -0.0644 3.75 0.670 -0.0679 2.66 0.556 -0.0698 1.63 0.447 -0.0738 0.44 0.327 -0.0758 -0.39 0.209 -0.0718 -1.41 0.079 -0.0652 -2.44 -0.050 -0.0586 -3.49 -0.181 -0.0484 -4.53 -0.294 -0.0438 -5.53 -0.383 -0.0440 -6.54 -0.470 -0.0422 -7.49 -0.533 -0.0198 -8.53 -0.553 0.0091 Tabulated from data in file ag02332.dat & reduced using program C06.01 Average Reynolds #: 300019 Number of angles of attack: 59 alpha / Cl / Cm -9.00 -0.575 0.0131 -7.85 -0.556 -0.0159 -6.95 -0.510 -0.0379 -5.86 -0.387 -0.0551 -4.97 -0.288 -0.0582 -3.77 -0.134 -0.0671 -2.70 0.017 -0.0782 -1.72 0.135 -0.0820 -0.83 0.218 -0.0770 0.59 0.341 -0.0658 1.43 0.452 -0.0705 2.35 0.550 -0.0707 3.25 0.646 -0.0696 4.29 0.744 -0.0668 5.29 0.833 -0.0636 6.28 0.920 -0.0607 7.54 1.026 -0.0562 8.34 1.085 -0.0527 9.33 1.159 -0.0483 10.39 1.218 -0.0422 11.42 1.262 -0.0357 12.42 1.284 -0.0303 13.50 1.292 -0.0307 14.20 0.975 -0.1511 15.23 0.938 -0.1519 16.17 0.936 -0.1542 17.20 0.928 -0.1574 18.22 0.936 -0.1665 19.24 1.005 -0.1756 20.17 1.028 -0.1830 19.71 1.020 -0.1715 18.75 0.975 -0.1638 17.77 0.956 -0.1604 16.70 0.933 -0.1560 15.76 0.917 -0.1533 14.75 0.912 -0.1484 13.78 0.976 -0.1508 12.80 1.038 -0.1336 11.97 1.280 -0.0304 10.84 1.246 -0.0370 9.89 1.196 -0.0426 8.82 1.124 -0.0480 7.78 1.047 -0.0526 6.73 0.962 -0.0571 5.81 0.884 -0.0605 4.47 0.760 -0.0648 3.70 0.690 -0.0676 2.55 0.573 -0.0698 1.51 0.459 -0.0698 0.59 0.341 -0.0653 -0.44 0.249 -0.0734 -1.37 0.165 -0.0801 -2.58 0.031 -0.0787 -3.45 -0.094 -0.0681 -4.60 -0.245 -0.0584 -5.55 -0.353 -0.0534 -6.77 -0.495 -0.0426 -7.74 -0.551 -0.0154 -8.54 -0.568 0.0054 Tabulated from data in file ag02334.dat & reduced using program C06.01 Average Reynolds #: 399591 Number of angles of attack: 47 alpha / Cl / Cm -9.00 -0.573 0.0182 -7.71 -0.558 -0.0171 -7.00 -0.498 -0.0430 -6.03 -0.363 -0.0654 -4.96 -0.242 -0.0687 -3.93 -0.111 -0.0761 -2.95 0.008 -0.0810 -1.88 0.115 -0.0801 -0.70 0.230 -0.0746 0.45 0.339 -0.0694 1.32 0.427 -0.0666 2.36 0.549 -0.0693 3.40 0.656 -0.0679 4.61 0.770 -0.0647 5.54 0.856 -0.0627 6.70 0.960 -0.0594 7.60 1.038 -0.0564 8.59 1.117 -0.0521 9.56 1.190 -0.0478 10.46 1.240 -0.0425 11.48 1.289 -0.0363 12.48 1.317 -0.0311 13.52 1.334 -0.0316 14.39 1.340 -0.0458 13.93 1.334 -0.0366 12.83 1.322 -0.0276 11.95 1.305 -0.0309 10.82 1.260 -0.0369 9.85 1.206 -0.0428 8.79 1.134 -0.0481 7.86 1.064 -0.0525 6.84 0.972 -0.0563 5.69 0.868 -0.0601 4.41 0.749 -0.0634 3.30 0.646 -0.0667 2.57 0.572 -0.0680 1.46 0.440 -0.0665 0.45 0.337 -0.0693 -0.56 0.242 -0.0742 -1.69 0.131 -0.0794 -2.66 0.038 -0.0815 -3.63 -0.076 -0.0779 -4.76 -0.218 -0.0700 -5.78 -0.333 -0.0656 -6.57 -0.437 -0.0581 -7.73 -0.553 -0.0174 -8.74 -0.575 0.0070 Tabulated from data in file ag02338.dat & reduced using program C06.01 Average Reynolds #: 500033 Number of angles of attack: 47 alpha / Cl / Cm -8.87 -0.564 0.0083 -8.31 -0.563 -0.0035 -7.06 -0.466 -0.0552 -5.94 -0.315 -0.0730 -4.92 -0.208 -0.0769 -3.96 -0.099 -0.0784 -2.82 0.018 -0.0778 -1.92 0.112 -0.0776 -0.89 0.217 -0.0743 0.16 0.325 -0.0711 1.42 0.452 -0.0671 2.29 0.551 -0.0668 3.24 0.652 -0.0671 4.27 0.747 -0.0636 5.36 0.853 -0.0615 6.54 0.964 -0.0587 7.76 1.074 -0.0547 8.84 1.157 -0.0497 9.72 1.220 -0.0456 10.73 1.273 -0.0427 11.65 1.310 -0.0385 12.64 1.337 -0.0355 13.52 1.355 -0.0391 14.67 1.347 -0.0579 13.98 1.363 -0.0427 12.89 1.357 -0.0249 11.91 1.334 -0.0294 10.87 1.286 -0.0345 9.78 1.226 -0.0419 8.68 1.145 -0.0473 7.74 1.069 -0.0513 6.59 0.966 -0.0562 5.44 0.858 -0.0598 4.46 0.764 -0.0620 3.55 0.676 -0.0642 2.53 0.573 -0.0660 1.44 0.452 -0.0663 0.23 0.331 -0.0704 -0.46 0.263 -0.0732 -1.52 0.149 -0.0758 -2.41 0.061 -0.0780 -3.46 -0.050 -0.0782 -4.48 -0.156 -0.0780 -5.47 -0.268 -0.0744 -6.54 -0.388 -0.0701 -7.52 -0.532 -0.0334 -8.58 -0.586 0.0015 Tabulated from data in file ag02339.dat & reduced using program C06.01 File sg6041.lft created using program C06.01 on Mon Feb 02 15:11:35 1998 :::::::::::::: SG6041T.LFT :::::::::::::: Airfoil: SG6041 Builder: M. Allen Comment: Zigzag trip Type C (h = 0.023") @ 2% u.s. & 5% l.s. Number of Reynolds #'s: 6 Average Reynolds #: 99900 Number of angles of attack: 59 alpha / Cl / Cm -8.94 -0.542 0.0183 -7.80 -0.525 -0.0032 -6.88 -0.501 -0.0325 -5.89 -0.439 -0.0437 -4.81 -0.361 -0.0410 -3.88 -0.279 -0.0392 -2.83 -0.176 -0.0408 -1.86 -0.076 -0.0431 -0.73 0.043 -0.0464 0.23 0.172 -0.0545 1.19 0.338 -0.0665 2.26 0.431 -0.0577 3.49 0.517 -0.0500 4.33 0.599 -0.0485 5.32 0.679 -0.0463 6.38 0.768 -0.0440 7.43 0.848 -0.0406 8.55 0.909 -0.0363 9.62 0.979 -0.0318 10.41 1.024 -0.0291 11.48 1.076 -0.0285 12.32 0.871 -0.1198 13.55 0.919 -0.1300 14.37 0.863 -0.1317 15.38 0.856 -0.1309 16.39 0.867 -0.1347 17.40 0.860 -0.1447 18.42 0.915 -0.1464 19.41 0.974 -0.1564 20.36 0.996 -0.1665 19.67 0.950 -0.1683 18.71 0.932 -0.1692 17.66 0.890 -0.1509 16.30 0.833 -0.1447 15.62 0.869 -0.1427 14.76 0.880 -0.1363 13.74 0.918 -0.1426 12.73 0.936 -0.1305 11.87 1.045 -0.0904 10.79 1.051 -0.0340 9.73 0.998 -0.0367 8.77 0.941 -0.0403 7.79 0.884 -0.0441 6.74 0.814 -0.0471 5.80 0.743 -0.0496 4.75 0.655 -0.0517 3.70 0.569 -0.0532 2.73 0.490 -0.0577 1.55 0.403 -0.0698 0.67 0.260 -0.0659 -0.50 0.081 -0.0514 -1.46 -0.022 -0.0464 -2.46 -0.118 -0.0437 -3.47 -0.220 -0.0420 -4.45 -0.314 -0.0411 -5.58 -0.400 -0.0441 -6.64 -0.475 -0.0431 -7.50 -0.528 -0.0228 -8.53 -0.551 0.0058 Tabulated from data in file pg02526.dat & reduced using program C06.01 Average Reynolds #: 149879 Number of angles of attack: 59 alpha / Cl / Cm -8.79 -0.564 0.0169 -7.78 -0.528 -0.0075 -6.89 -0.499 -0.0250 -5.79 -0.412 -0.0446 -4.75 -0.331 -0.0414 -3.86 -0.247 -0.0422 -2.84 -0.147 -0.0448 -1.72 0.011 -0.0555 -0.71 0.189 -0.0732 0.32 0.291 -0.0675 1.26 0.365 -0.0602 2.27 0.440 -0.0571 3.33 0.529 -0.0534 4.29 0.608 -0.0494 5.38 0.703 -0.0466 6.57 0.803 -0.0433 7.41 0.876 -0.0407 8.55 0.956 -0.0366 9.70 1.022 -0.0314 10.81 1.068 -0.0270 11.50 1.094 -0.0243 12.36 1.022 -0.1046 13.47 0.988 -0.1377 14.42 0.975 -0.1453 15.54 0.891 -0.1401 16.48 0.869 -0.1379 17.45 0.874 -0.1483 18.47 0.927 -0.1471 19.58 0.993 -0.1588 20.51 0.973 -0.1684 19.54 0.974 -0.1794 18.57 0.913 -0.1746 17.56 0.901 -0.1521 16.62 0.865 -0.1391 15.63 0.903 -0.1437 14.53 0.920 -0.1445 13.54 1.032 -0.1387 12.74 1.025 -0.1230 11.90 1.116 -0.0315 10.89 1.077 -0.0321 9.82 1.030 -0.0361 8.85 0.983 -0.0407 7.87 0.923 -0.0439 6.80 0.841 -0.0472 5.80 0.752 -0.0496 4.73 0.660 -0.0521 3.76 0.574 -0.0548 2.72 0.487 -0.0589 1.62 0.399 -0.0611 0.50 0.311 -0.0678 -0.42 0.243 -0.0768 -1.51 0.059 -0.0631 -2.47 -0.097 -0.0480 -3.52 -0.212 -0.0435 -4.51 -0.307 -0.0420 -5.53 -0.385 -0.0444 -6.57 -0.468 -0.0408 -7.51 -0.518 -0.0209 -8.47 -0.515 0.0068 Tabulated from data in file pg02527.dat & reduced using program C06.01 Average Reynolds #: 199919 Number of angles of attack: 59 alpha / Cl / Cm -8.86 -0.550 0.0206 -7.88 -0.555 -0.0030 -6.91 -0.506 -0.0287 -5.83 -0.418 -0.0434 -4.71 -0.315 -0.0419 -3.71 -0.209 -0.0451 -2.68 -0.080 -0.0527 -1.74 0.091 -0.0709 -0.68 0.204 -0.0686 0.26 0.275 -0.0618 1.31 0.371 -0.0589 2.26 0.457 -0.0574 3.36 0.558 -0.0556 4.32 0.648 -0.0539 5.32 0.738 -0.0486 6.35 0.825 -0.0459 7.68 0.925 -0.0415 8.34 0.970 -0.0387 9.96 1.058 -0.0321 10.68 1.091 -0.0294 11.40 1.114 -0.0265 12.50 1.140 -0.0248 13.34 1.063 -0.1308 14.68 0.974 -0.1430 15.72 0.925 -0.1395 16.44 0.876 -0.1455 17.53 0.937 -0.1513 18.46 0.972 -0.1542 19.42 0.984 -0.1606 20.49 0.993 -0.1733 19.54 0.995 -0.1799 18.36 0.919 -0.1512 17.35 0.942 -0.1524 16.36 0.902 -0.1494 15.45 0.912 -0.1493 14.52 0.991 -0.1495 13.47 1.012 -0.1375 12.67 1.072 -0.1133 11.86 1.127 -0.0285 10.81 1.098 -0.0308 9.90 1.060 -0.0346 8.85 1.001 -0.0390 7.76 0.932 -0.0431 6.81 0.865 -0.0461 5.75 0.778 -0.0495 4.75 0.695 -0.0537 3.73 0.595 -0.0564 2.58 0.490 -0.0577 1.68 0.403 -0.0586 0.64 0.305 -0.0607 -0.55 0.208 -0.0677 -1.41 0.139 -0.0739 -2.45 -0.050 -0.0556 -3.49 -0.190 -0.0450 -4.53 -0.302 -0.0408 -5.74 -0.409 -0.0423 -6.60 -0.482 -0.0370 -7.57 -0.535 -0.0137 -8.55 -0.561 0.0106 Tabulated from data in file pg02529.dat & reduced using program C06.01 Average Reynolds #: 299890 Number of angles of attack: 59 alpha / Cl / Cm -9.02 -0.587 0.0193 -7.83 -0.555 -0.0148 -6.77 -0.508 -0.0384 -5.68 -0.389 -0.0512 -4.76 -0.284 -0.0556 -3.77 -0.111 -0.0704 -2.82 -0.014 -0.0698 -1.51 0.102 -0.0650 -0.48 0.202 -0.0646 0.40 0.288 -0.0633 1.50 0.409 -0.0619 2.52 0.512 -0.0605 3.40 0.593 -0.0590 4.43 0.692 -0.0574 5.47 0.784 -0.0533 6.40 0.864 -0.0512 7.58 0.950 -0.0458 8.62 1.018 -0.0407 9.44 1.066 -0.0365 10.51 1.114 -0.0316 11.51 1.142 -0.0287 12.39 1.155 -0.0316 13.08 1.147 -0.1113 14.26 1.046 -0.1362 15.23 1.003 -0.1421 16.18 0.979 -0.1582 17.19 1.013 -0.1565 18.23 0.946 -0.1752 19.20 1.001 -0.1707 20.20 0.991 -0.1746 19.72 0.979 -0.1666 18.70 0.959 -0.1618 17.60 0.989 -0.1597 16.72 0.955 -0.1520 15.66 0.963 -0.1520 14.58 0.974 -0.1491 13.83 1.091 -0.1330 12.64 1.135 -0.0368 11.82 1.130 -0.0316 10.80 1.117 -0.0308 9.85 1.082 -0.0337 8.85 1.030 -0.0384 7.86 0.974 -0.0436 6.78 0.898 -0.0490 5.78 0.818 -0.0527 4.74 0.725 -0.0556 3.61 0.623 -0.0595 2.54 0.516 -0.0608 1.58 0.419 -0.0623 0.45 0.302 -0.0633 -0.60 0.186 -0.0644 -2.02 0.053 -0.0652 -2.74 -0.009 -0.0692 -3.61 -0.092 -0.0722 -4.74 -0.281 -0.0555 -5.76 -0.398 -0.0507 -6.73 -0.502 -0.0412 -7.64 -0.551 -0.0190 -8.63 -0.576 0.0072 Tabulated from data in file pg02530.dat & reduced using program C06.01 Average Reynolds #: 399464 Number of angles of attack: 41 alpha / Cl / Cm -7.00 -0.514 -0.0379 -5.95 -0.374 -0.0622 -5.00 -0.253 -0.0668 -3.94 -0.131 -0.0669 -2.94 -0.042 -0.0648 -1.88 0.065 -0.0645 -0.88 0.169 -0.0637 0.29 0.294 -0.0620 1.21 0.394 -0.0612 2.27 0.498 -0.0598 3.36 0.605 -0.0580 4.60 0.721 -0.0554 5.49 0.806 -0.0528 6.45 0.889 -0.0501 7.48 0.967 -0.0463 8.35 1.027 -0.0421 9.87 1.109 -0.0347 10.37 1.131 -0.0327 11.43 1.170 -0.0307 12.38 1.191 -0.0306 13.11 1.068 -0.1141 12.99 1.187 -0.1142 11.93 1.181 -0.0324 10.82 1.148 -0.0325 9.86 1.110 -0.0353 8.87 1.055 -0.0401 7.85 0.991 -0.0440 6.68 0.905 -0.0492 5.78 0.828 -0.0520 4.70 0.730 -0.0554 3.47 0.614 -0.0581 2.45 0.514 -0.0600 1.48 0.417 -0.0613 0.63 0.330 -0.0626 -0.41 0.227 -0.0637 -1.44 0.104 -0.0648 -2.58 -0.010 -0.0651 -3.44 -0.092 -0.0660 -4.48 -0.183 -0.0703 -5.56 -0.327 -0.0634 -6.51 -0.443 -0.0557 Tabulated from data in file pg02532.dat & reduced using program C06.01 Average Reynolds #: 500193 Number of angles of attack: 37 alpha / Cl / Cm -5.95 -0.341 -0.0709 -4.84 -0.225 -0.0694 -3.83 -0.130 -0.0667 -2.87 -0.038 -0.0658 -1.81 0.071 -0.0646 -0.87 0.187 -0.0633 0.31 0.309 -0.0625 1.19 0.403 -0.0613 2.27 0.513 -0.0589 3.26 0.612 -0.0579 4.32 0.710 -0.0541 5.54 0.824 -0.0502 6.75 0.926 -0.0465 7.70 0.999 -0.0430 8.51 1.051 -0.0395 9.39 1.101 -0.0360 10.67 1.146 -0.0333 11.41 1.169 -0.0331 12.39 1.196 -0.0386 11.92 1.183 -0.0365 10.89 1.156 -0.0332 9.77 1.111 -0.0351 8.84 1.065 -0.0383 7.87 1.007 -0.0421 6.83 0.927 -0.0460 5.67 0.833 -0.0504 4.56 0.733 -0.0540 3.38 0.620 -0.0564 2.63 0.548 -0.0587 1.69 0.453 -0.0602 0.57 0.336 -0.0616 -0.49 0.225 -0.0629 -1.38 0.132 -0.0637 -2.49 0.001 -0.0645 -3.49 -0.098 -0.0655 -4.50 -0.195 -0.0671 -5.55 -0.291 -0.0718 Tabulated from data in file pg02533.dat & reduced using program C06.01 File sg6041t.lft created using program C06.01 on Mon Feb 02 15:11:35 1998 :::::::::::::: SG6042.LFT :::::::::::::: Airfoil: SG6042 Builder: M. Allen Comment: clean Number of Reynolds #'s: 6 Average Reynolds #: 99991 Number of angles of attack: 59 alpha / Cl / Cm -8.91 -0.428 0.0200 -7.99 -0.430 0.0162 -7.03 -0.438 0.0078 -5.97 -0.437 -0.0140 -4.99 -0.320 -0.0618 -3.96 -0.157 -0.0815 -2.91 -0.010 -0.0936 -1.86 0.126 -0.1062 -0.88 0.214 -0.1053 0.07 0.301 -0.1109 1.07 0.397 -0.1143 2.08 0.493 -0.1202 3.35 0.687 -0.1296 4.32 0.814 -0.1289 5.26 0.912 -0.1219 6.31 1.002 -0.1154 7.31 1.094 -0.1102 8.31 1.167 -0.1008 9.49 1.230 -0.0919 10.43 1.281 -0.0852 11.39 1.321 -0.0790 12.47 1.345 -0.0718 13.41 1.346 -0.0674 14.22 1.010 -0.1697 15.20 0.987 -0.1801 16.24 0.995 -0.1823 17.34 1.040 -0.1852 18.44 1.083 -0.1891 19.26 1.061 -0.1892 20.27 1.076 -0.2038 19.63 1.067 -0.2036 18.64 1.026 -0.1926 17.63 1.065 -0.1860 16.49 1.009 -0.1905 15.61 1.019 -0.1887 14.58 0.982 -0.1819 13.61 1.003 -0.1835 12.89 1.358 -0.0819 11.76 1.334 -0.0801 10.83 1.311 -0.0867 9.76 1.265 -0.0940 8.76 1.213 -0.1007 7.75 1.162 -0.1097 6.60 1.071 -0.1165 5.66 0.982 -0.1224 4.64 0.875 -0.1300 3.63 0.729 -0.1324 2.39 0.543 -0.1228 1.42 0.444 -0.1153 0.53 0.381 -0.1162 -0.56 0.273 -0.1078 -1.54 0.188 -0.1071 -2.68 0.048 -0.0941 -3.57 -0.074 -0.0857 -4.61 -0.242 -0.0729 -5.62 -0.404 -0.0332 -6.58 -0.455 -0.0049 -7.60 -0.459 0.0070 -8.50 -0.415 0.0114 Tabulated from data in file ag02341.dat & reduced using program C06.01 Average Reynolds #: 149827 Number of angles of attack: 59 alpha / Cl / Cm -8.83 -0.371 0.0171 -7.78 -0.372 0.0114 -6.70 -0.387 0.0010 -5.79 -0.342 -0.0192 -4.84 -0.216 -0.0725 -3.74 -0.069 -0.0935 -2.73 0.059 -0.1051 -1.67 0.173 -0.1176 -0.62 0.273 -0.1188 0.21 0.367 -0.1241 1.44 0.498 -0.1273 2.47 0.605 -0.1270 3.44 0.698 -0.1236 4.40 0.789 -0.1192 5.55 0.903 -0.1169 6.43 0.982 -0.1120 7.44 1.049 -0.1055 8.63 1.112 -0.0965 9.57 1.168 -0.0897 10.44 1.218 -0.0833 11.57 1.266 -0.0752 12.67 1.289 -0.0676 13.44 1.290 -0.0636 14.24 0.957 -0.1733 15.55 0.961 -0.1839 16.43 0.956 -0.1832 17.56 0.953 -0.1839 18.54 0.978 -0.1907 19.52 0.990 -0.1983 20.44 0.983 -0.2019 19.21 0.982 -0.1980 18.32 0.954 -0.1898 17.29 0.956 -0.1936 16.19 0.938 -0.1975 15.40 0.946 -0.1861 14.38 0.950 -0.1781 13.48 0.993 -0.1671 12.77 1.294 -0.0682 11.83 1.275 -0.0740 10.67 1.235 -0.0817 9.70 1.188 -0.0878 8.68 1.120 -0.0944 7.68 1.062 -0.1011 6.38 0.976 -0.1082 5.68 0.922 -0.1120 4.56 0.808 -0.1151 3.61 0.715 -0.1168 2.47 0.606 -0.1233 1.45 0.495 -0.1235 0.25 0.354 -0.1214 -0.58 0.247 -0.1170 -1.61 0.132 -0.1168 -2.74 -0.009 -0.1031 -3.78 -0.141 -0.0884 -4.87 -0.292 -0.0679 -5.63 -0.369 -0.0296 -6.66 -0.398 -0.0014 -7.57 -0.392 0.0133 -8.53 -0.375 0.0139 Tabulated from data in file pg02502.dat & reduced using program C06.01 Average Reynolds #: 200028 Number of angles of attack: 59 alpha / Cl / Cm -8.98 -0.407 0.0178 -7.99 -0.453 0.0183 -6.92 -0.452 -0.0014 -5.95 -0.376 -0.0369 -4.96 -0.177 -0.0926 -3.82 -0.003 -0.1096 -2.82 0.141 -0.1219 -1.41 0.304 -0.1323 -0.91 0.364 -0.1330 0.41 0.501 -0.1295 1.31 0.600 -0.1285 2.31 0.702 -0.1264 3.42 0.816 -0.1227 4.35 0.906 -0.1199 5.41 1.006 -0.1160 6.50 1.095 -0.1104 7.38 1.157 -0.1048 8.49 1.228 -0.0969 9.46 1.285 -0.0901 10.50 1.341 -0.0820 11.39 1.373 -0.0753 12.47 1.403 -0.0675 13.45 1.414 -0.0618 14.38 1.414 -0.0597 14.89 1.049 -0.1792 16.14 1.059 -0.1859 17.11 1.074 -0.1921 18.16 1.084 -0.1889 19.21 1.123 -0.1918 20.40 1.099 -0.2042 19.50 1.116 -0.2048 18.57 1.082 -0.1950 17.58 1.045 -0.1887 16.55 1.058 -0.1899 15.69 1.045 -0.1879 14.53 1.031 -0.1855 13.89 1.419 -0.0620 12.82 1.407 -0.0656 11.79 1.389 -0.0732 10.83 1.353 -0.0805 9.80 1.305 -0.0879 8.66 1.242 -0.0962 7.70 1.184 -0.1034 6.57 1.103 -0.1101 5.65 1.027 -0.1143 4.53 0.924 -0.1193 3.49 0.820 -0.1219 2.46 0.719 -0.1252 1.45 0.611 -0.1277 0.38 0.497 -0.1293 -0.57 0.393 -0.1313 -1.71 0.266 -0.1315 -2.90 0.115 -0.1191 -3.85 -0.015 -0.1068 -4.65 -0.119 -0.0990 -5.60 -0.311 -0.0611 -6.58 -0.436 -0.0076 -7.54 -0.464 0.0101 -8.63 -0.411 0.0126 Tabulated from data in file cl02344.dat & reduced using program C06.01 Average Reynolds #: 299834 Number of angles of attack: 59 alpha / Cl / Cm -8.93 -0.429 0.0162 -8.02 -0.432 0.0060 -7.05 -0.399 -0.0233 -6.00 -0.238 -0.0917 -5.05 -0.068 -0.1221 -4.05 0.062 -0.1298 -2.95 0.176 -0.1332 -1.98 0.286 -0.1351 -0.98 0.390 -0.1336 0.13 0.483 -0.1263 1.21 0.601 -0.1263 2.09 0.697 -0.1258 3.16 0.810 -0.1244 4.15 0.908 -0.1221 5.34 1.017 -0.1178 6.38 1.101 -0.1129 7.37 1.180 -0.1073 8.30 1.243 -0.1011 9.46 1.315 -0.0931 10.40 1.366 -0.0867 11.63 1.413 -0.0767 12.42 1.441 -0.0718 13.44 1.458 -0.0661 14.49 1.467 -0.0645 15.54 1.467 -0.0703 16.47 1.445 -0.0818 17.08 1.026 -0.1908 18.12 1.055 -0.1942 19.12 1.047 -0.1977 20.04 1.071 -0.2118 19.66 1.076 -0.2176 18.62 1.059 -0.2056 17.61 1.040 -0.1961 16.61 1.065 -0.1902 15.62 1.060 -0.1877 14.68 1.147 -0.1813 13.77 1.452 -0.0644 12.62 1.442 -0.0674 11.78 1.420 -0.0730 10.58 1.372 -0.0817 9.78 1.330 -0.0872 8.52 1.257 -0.0966 7.55 1.192 -0.1029 6.63 1.125 -0.1086 5.77 1.059 -0.1136 4.65 0.958 -0.1184 3.68 0.864 -0.1215 2.62 0.758 -0.1238 1.60 0.639 -0.1249 0.57 0.530 -0.1257 -0.47 0.431 -0.1302 -1.50 0.334 -0.1355 -2.52 0.221 -0.1344 -3.61 0.095 -0.1304 -4.63 -0.016 -0.1243 -5.68 -0.175 -0.1074 -6.61 -0.348 -0.0520 -7.49 -0.438 -0.0061 -8.47 -0.439 0.0095 Tabulated from data in file cl02346.dat & reduced using program C06.01 Average Reynolds #: 400093 Number of angles of attack: 59 alpha / Cl / Cm -8.88 -0.439 0.0127 -8.37 -0.433 0.0030 -7.15 -0.335 -0.0548 -6.14 -0.167 -0.1134 -5.04 -0.017 -0.1315 -4.09 0.068 -0.1320 -3.02 0.179 -0.1324 -2.02 0.288 -0.1316 -0.94 0.399 -0.1315 0.05 0.489 -0.1274 1.18 0.605 -0.1265 2.12 0.709 -0.1264 3.13 0.816 -0.1256 4.18 0.919 -0.1230 5.24 1.014 -0.1189 6.36 1.102 -0.1130 7.39 1.190 -0.1084 8.29 1.248 -0.1026 9.57 1.335 -0.0952 10.46 1.379 -0.0884 11.55 1.426 -0.0804 12.61 1.461 -0.0735 13.60 1.478 -0.0683 14.44 1.491 -0.0679 15.48 1.495 -0.0730 15.99 1.488 -0.0742 16.52 1.474 -0.0812 17.51 1.448 -0.0923 18.91 1.074 -0.2029 20.02 1.099 -0.2131 19.53 1.048 -0.2083 18.80 1.063 -0.2028 17.70 1.058 -0.2131 16.83 1.084 -0.2011 16.00 1.083 -0.1972 15.72 1.066 -0.1957 13.85 1.476 -0.0634 12.76 1.454 -0.0673 11.80 1.432 -0.0735 10.61 1.387 -0.0819 9.41 1.321 -0.0902 8.64 1.273 -0.0951 7.64 1.203 -0.1019 6.61 1.123 -0.1077 5.62 1.044 -0.1133 4.60 0.956 -0.1176 3.66 0.867 -0.1202 2.56 0.759 -0.1233 1.63 0.652 -0.1237 0.54 0.536 -0.1244 -0.45 0.444 -0.1294 -1.48 0.337 -0.1312 -2.51 0.230 -0.1314 -3.55 0.118 -0.1319 -4.68 0.020 -0.1314 -5.60 -0.085 -0.1284 -6.58 -0.245 -0.0893 -7.49 -0.380 -0.0392 -8.37 -0.433 0.0042 Tabulated from data in file cl02348.dat & reduced using program C06.01 Average Reynolds #: 499434 Number of angles of attack: 49 alpha / Cl / Cm -6.01 -0.124 -0.1217 -4.99 -0.010 -0.1282 -4.03 0.071 -0.1283 -2.91 0.190 -0.1287 -1.94 0.296 -0.1288 -0.94 0.405 -0.1295 0.17 0.514 -0.1264 1.21 0.622 -0.1255 2.17 0.724 -0.1228 3.18 0.831 -0.1217 4.27 0.935 -0.1188 5.21 1.015 -0.1154 6.24 1.103 -0.1114 7.24 1.184 -0.1052 8.34 1.269 -0.1000 9.31 1.335 -0.0948 10.46 1.395 -0.0882 11.65 1.450 -0.0797 13.05 1.484 -0.0725 13.81 1.496 -0.0697 14.72 1.505 -0.0726 15.43 1.513 -0.0767 16.43 1.502 -0.0868 17.46 1.468 -0.0953 18.31 1.441 -0.1054 17.66 1.461 -0.0987 16.20 1.490 -0.0818 15.64 1.520 -0.0759 14.83 1.520 -0.0647 13.83 1.511 -0.0605 12.74 1.487 -0.0665 11.77 1.457 -0.0718 10.46 1.396 -0.0813 9.53 1.340 -0.0874 8.57 1.280 -0.0950 7.74 1.219 -0.0995 6.65 1.134 -0.1053 5.58 1.047 -0.1112 4.64 0.967 -0.1151 3.59 0.866 -0.1183 2.54 0.763 -0.1207 1.54 0.650 -0.1210 0.47 0.543 -0.1234 -0.45 0.451 -0.1271 -1.66 0.324 -0.1284 -2.46 0.235 -0.1282 -3.48 0.123 -0.1281 -4.74 0.009 -0.1274 -5.61 -0.075 -0.1279 Tabulated from data in file cl02350.dat & reduced using program C06.01 File sg6042.lft created using program C06.01 on Mon Feb 02 15:11:35 1998 :::::::::::::: SG6042T.LFT :::::::::::::: Airfoil: SG6042 Builder: M. Allen Comment: Zigzag trip Type C (h = 0.023") @ 2% u.s. & 5% l.s. (Cm @ 500,000 is incorrect) Number of Reynolds #'s: 6 Average Reynolds #: 99944 Number of angles of attack: 59 alpha / Cl / Cm -8.92 -0.416 0.0175 -7.80 -0.428 0.0114 -6.85 -0.429 0.0058 -5.81 -0.403 -0.0159 -4.86 -0.281 -0.0603 -3.94 -0.151 -0.0776 -2.89 -0.026 -0.0863 -1.89 0.112 -0.0979 -0.58 0.262 -0.1052 0.23 0.323 -0.1093 1.36 0.495 -0.1143 2.28 0.632 -0.1129 3.39 0.710 -0.1008 4.32 0.777 -0.0946 5.36 0.845 -0.0905 6.35 0.910 -0.0872 7.46 0.983 -0.0826 8.42 1.034 -0.0777 9.59 1.108 -0.0722 10.41 1.148 -0.0683 11.38 1.186 -0.0636 12.53 1.231 -0.0594 13.54 1.256 -0.0589 14.20 0.948 -0.1687 15.34 0.979 -0.1706 16.36 1.011 -0.1746 17.30 0.971 -0.1767 18.40 0.982 -0.1864 19.37 1.009 -0.1963 20.47 1.071 -0.2048 19.48 1.055 -0.2106 18.55 0.993 -0.1873 17.51 0.977 -0.1869 16.45 0.982 -0.1842 15.59 0.997 -0.1811 14.61 1.010 -0.1814 13.82 1.195 -0.0716 12.83 1.248 -0.0621 11.81 1.219 -0.0657 10.82 1.186 -0.0698 9.83 1.140 -0.0744 8.81 1.086 -0.0798 7.60 1.011 -0.0852 6.68 0.956 -0.0885 5.61 0.881 -0.0920 4.70 0.817 -0.0955 3.56 0.745 -0.1019 2.61 0.695 -0.1108 1.50 0.548 -0.1212 0.55 0.387 -0.1131 -0.53 0.292 -0.1097 -1.63 0.164 -0.1029 -2.52 0.036 -0.0919 -3.60 -0.103 -0.0811 -4.58 -0.227 -0.0706 -5.59 -0.383 -0.0342 -6.58 -0.419 -0.0072 -7.59 -0.416 0.0057 -8.51 -0.406 0.0101 Tabulated from data in file pg02547.dat & reduced using program C06.01 Average Reynolds #: 150023 Number of angles of attack: 59 alpha / Cl / Cm -8.63 -0.422 0.0184 -7.88 -0.423 0.0161 -6.97 -0.436 0.0099 -5.95 -0.418 -0.0119 -4.94 -0.270 -0.0652 -3.80 -0.079 -0.0895 -2.85 0.048 -0.0994 -1.70 0.206 -0.1133 -0.64 0.350 -0.1197 0.29 0.469 -0.1204 1.30 0.551 -0.1113 2.36 0.634 -0.1054 3.39 0.715 -0.1021 4.39 0.788 -0.0977 5.31 0.860 -0.0930 6.49 0.954 -0.0883 7.48 1.030 -0.0837 8.47 1.094 -0.0786 9.42 1.149 -0.0729 10.47 1.192 -0.0673 11.47 1.224 -0.0618 12.36 1.243 -0.0594 13.34 1.266 -0.0600 14.44 1.271 -0.0658 15.31 1.078 -0.1788 16.43 1.046 -0.1799 17.35 0.983 -0.1802 18.52 1.035 -0.1829 19.49 1.061 -0.1971 20.48 1.069 -0.2021 19.02 1.029 -0.1937 18.43 1.012 -0.1944 17.48 0.982 -0.1858 16.47 1.029 -0.1847 15.51 1.036 -0.1841 14.48 1.133 -0.1675 13.86 1.280 -0.0669 12.83 1.258 -0.0631 11.81 1.237 -0.0648 10.80 1.210 -0.0689 9.66 1.165 -0.0751 8.74 1.114 -0.0799 7.57 1.047 -0.0856 6.69 0.980 -0.0894 5.63 0.894 -0.0933 4.64 0.815 -0.0974 3.48 0.728 -0.1028 2.57 0.655 -0.1055 1.56 0.581 -0.1104 0.54 0.500 -0.1196 -0.54 0.377 -0.1248 -1.55 0.232 -0.1156 -2.57 0.093 -0.1049 -3.68 -0.061 -0.0915 -4.76 -0.227 -0.0755 -6.06 -0.418 -0.0196 -6.56 -0.424 -0.0044 -7.55 -0.424 0.0068 -8.51 -0.419 0.0110 Tabulated from data in file pg02548.dat & reduced using program C06.01 Average Reynolds #: 199776 Number of angles of attack: 59 alpha / Cl / Cm -8.75 -0.413 0.0139 -8.00 -0.426 0.0171 -6.88 -0.448 -0.0011 -5.89 -0.382 -0.0390 -4.82 -0.180 -0.0915 -3.57 0.015 -0.1095 -2.76 0.134 -0.1175 -1.73 0.276 -0.1256 -0.32 0.421 -0.1193 0.35 0.472 -0.1147 1.56 0.573 -0.1096 2.29 0.636 -0.1067 3.34 0.730 -0.1043 4.37 0.817 -0.1013 5.48 0.909 -0.0974 6.45 0.976 -0.0916 7.38 1.042 -0.0864 8.49 1.111 -0.0806 9.54 1.165 -0.0748 10.48 1.203 -0.0696 11.42 1.231 -0.0650 12.43 1.248 -0.0629 13.37 1.269 -0.0644 14.53 1.279 -0.0724 15.39 1.277 -0.0859 16.03 1.005 -0.1836 17.33 1.086 -0.1893 18.28 1.050 -0.1919 19.29 1.090 -0.1976 20.29 1.121 -0.2106 19.37 1.052 -0.2073 18.45 1.017 -0.1919 17.52 1.095 -0.1891 16.44 1.071 -0.1871 15.11 1.051 -0.1712 14.46 1.039 -0.1742 13.81 1.279 -0.0687 12.86 1.262 -0.0648 11.82 1.245 -0.0658 10.77 1.218 -0.0692 9.79 1.185 -0.0746 8.73 1.130 -0.0808 7.59 1.063 -0.0873 6.58 0.997 -0.0932 5.66 0.930 -0.0979 4.59 0.841 -0.1015 3.46 0.743 -0.1048 2.47 0.650 -0.1067 1.51 0.569 -0.1101 0.24 0.463 -0.1155 -0.69 0.388 -0.1226 -1.75 0.269 -0.1255 -2.72 0.137 -0.1189 -4.28 -0.078 -0.1005 -5.19 -0.248 -0.0761 -5.62 -0.337 -0.0503 -6.55 -0.435 -0.0092 -7.55 -0.441 0.0061 -8.49 -0.420 0.0161 Tabulated from data in file pg02550.dat & reduced using program C06.01 Average Reynolds #: 299892 Number of angles of attack: 59 alpha / Cl / Cm -8.85 -0.431 0.0149 -7.88 -0.443 0.0013 -6.83 -0.379 -0.0364 -6.03 -0.263 -0.0789 -5.06 -0.075 -0.1199 -4.05 0.065 -0.1292 -3.04 0.163 -0.1260 -2.00 0.245 -0.1177 -0.95 0.352 -0.1162 0.03 0.440 -0.1134 1.09 0.545 -0.1116 2.09 0.638 -0.1101 3.22 0.743 -0.1077 4.43 0.851 -0.1039 5.30 0.926 -0.1009 6.42 1.014 -0.0963 7.70 1.105 -0.0899 8.57 1.158 -0.0845 9.54 1.207 -0.0780 10.55 1.242 -0.0721 11.52 1.268 -0.0677 12.49 1.283 -0.0672 13.58 1.298 -0.0732 14.50 1.319 -0.0914 15.19 1.108 -0.1785 16.09 1.086 -0.1840 17.09 1.123 -0.1831 18.16 1.101 -0.1882 19.05 1.059 -0.2029 20.10 1.083 -0.2045 19.69 1.103 -0.2046 18.46 1.059 -0.1948 17.72 1.147 -0.1977 16.61 1.096 -0.1909 15.78 1.085 -0.1868 14.80 1.099 -0.1764 13.73 1.302 -0.0764 12.54 1.289 -0.0675 11.66 1.275 -0.0671 10.64 1.248 -0.0700 9.72 1.212 -0.0748 8.62 1.162 -0.0824 7.58 1.100 -0.0891 6.41 1.013 -0.0941 5.33 0.929 -0.0991 4.44 0.854 -0.1025 3.44 0.764 -0.1056 2.34 0.660 -0.1084 1.48 0.579 -0.1107 0.54 0.491 -0.1131 -0.59 0.386 -0.1159 -1.52 0.292 -0.1167 -2.46 0.206 -0.1212 -3.55 0.118 -0.1295 -4.57 -0.012 -0.1245 -5.61 -0.176 -0.1059 -6.77 -0.374 -0.0413 -7.75 -0.449 -0.0034 -8.45 -0.436 0.0116 Tabulated from data in file pg02551.dat & reduced using program C06.01 Average Reynolds #: 399775 Number of angles of attack: 43 alpha / Cl / Cm -7.21 -0.359 -0.0464 -6.16 -0.189 -0.1083 -5.04 -0.035 -0.1280 -4.05 0.048 -0.1208 -3.02 0.136 -0.1160 -1.97 0.247 -0.1165 -0.98 0.344 -0.1152 0.06 0.442 -0.1132 1.08 0.546 -0.1118 2.13 0.646 -0.1098 3.18 0.746 -0.1075 4.15 0.839 -0.1049 5.25 0.932 -0.1011 6.25 1.019 -0.0968 7.41 1.097 -0.0899 8.31 1.155 -0.0859 9.57 1.222 -0.0784 10.84 1.272 -0.0723 11.85 1.297 -0.0692 12.83 1.316 -0.0696 13.72 1.321 -0.0767 14.53 1.330 -0.0858 13.47 1.320 -0.0742 12.74 1.311 -0.0695 11.77 1.296 -0.0689 10.60 1.262 -0.0721 9.42 1.215 -0.0775 8.32 1.157 -0.0841 7.59 1.109 -0.0879 6.57 1.036 -0.0935 5.50 0.954 -0.0983 4.64 0.877 -0.1019 3.56 0.782 -0.1054 2.52 0.684 -0.1076 1.56 0.591 -0.1097 0.55 0.490 -0.1115 -0.50 0.393 -0.1131 -1.53 0.288 -0.1157 -2.51 0.189 -0.1166 -3.59 0.081 -0.1181 -4.57 0.011 -0.1275 -5.65 -0.113 -0.1252 -6.62 -0.252 -0.0939 Tabulated from data in file pg02554.dat & reduced using program C06.01 Average Reynolds #: 499853 Number of angles of attack: 41 alpha / Cl / Cm -6.11 -0.194 -0.0382 -4.90 -0.045 -0.0457 -3.97 0.037 -0.0452 -2.94 0.144 -0.0428 -1.87 0.255 -0.0421 -0.91 0.352 -0.0428 0.12 0.451 -0.0436 1.15 0.556 -0.0446 2.18 0.658 -0.0453 3.19 0.752 -0.0458 4.25 0.852 -0.0459 5.28 0.941 -0.0453 6.30 1.027 -0.0446 7.32 1.103 -0.0433 8.47 1.171 -0.0417 9.35 1.221 -0.0404 10.67 1.270 -0.0385 11.61 1.300 -0.0378 12.86 1.331 -0.0385 13.58 1.341 -0.0404 14.39 1.342 -0.0449 13.40 1.342 -0.0395 12.53 1.322 -0.0366 11.57 1.295 -0.0363 10.34 1.255 -0.0374 9.11 1.204 -0.0393 8.05 1.146 -0.0415 7.68 1.122 -0.0421 6.59 1.048 -0.0435 5.73 0.980 -0.0444 4.69 0.890 -0.0455 3.66 0.796 -0.0457 2.63 0.700 -0.0458 1.68 0.608 -0.0449 0.61 0.502 -0.0443 -0.43 0.401 -0.0430 -1.43 0.297 -0.0424 -2.51 0.188 -0.0418 -3.45 0.093 -0.0415 -4.52 -0.012 -0.0452 -5.53 -0.118 -0.0443 Tabulated from data in file pg02555.dat & reduced using program C06.01 File sg6042t.lft created using program C06.01 on Mon Feb 02 15:11:35 1998 :::::::::::::: SG6042T2.LFT :::::::::::::: Airfoil: SG6042 Builder: M. Allen Comment: Re = 300,000: clean & zigzag trip Type C @ 2% u.s. & 5% l.s. (h = 0.005", 0.010", 0.014", 0.018", 0.023") Number of Reynolds #'s: 6 Average Reynolds #: 299834 Number of angles of attack: 59 alpha / Cl / Cm -8.93 -0.429 0.0162 -8.02 -0.432 0.0060 -7.05 -0.399 -0.0233 -6.00 -0.238 -0.0917 -5.05 -0.068 -0.1221 -4.05 0.062 -0.1298 -2.95 0.176 -0.1332 -1.98 0.286 -0.1351 -0.98 0.390 -0.1336 0.13 0.483 -0.1263 1.21 0.601 -0.1263 2.09 0.697 -0.1258 3.16 0.810 -0.1244 4.15 0.908 -0.1221 5.34 1.017 -0.1178 6.38 1.101 -0.1129 7.37 1.180 -0.1073 8.30 1.243 -0.1011 9.46 1.315 -0.0931 10.40 1.366 -0.0867 11.63 1.413 -0.0767 12.42 1.441 -0.0718 13.44 1.458 -0.0661 14.49 1.467 -0.0645 15.54 1.467 -0.0703 16.47 1.445 -0.0818 17.08 1.026 -0.1908 18.12 1.055 -0.1942 19.12 1.047 -0.1977 20.04 1.071 -0.2118 19.66 1.076 -0.2176 18.62 1.059 -0.2056 17.61 1.040 -0.1961 16.61 1.065 -0.1902 15.62 1.060 -0.1877 14.68 1.147 -0.1813 13.77 1.452 -0.0644 12.62 1.442 -0.0674 11.78 1.420 -0.0730 10.58 1.372 -0.0817 9.78 1.330 -0.0872 8.52 1.257 -0.0966 7.55 1.192 -0.1029 6.63 1.125 -0.1086 5.77 1.059 -0.1136 4.65 0.958 -0.1184 3.68 0.864 -0.1215 2.62 0.758 -0.1238 1.60 0.639 -0.1249 0.57 0.530 -0.1257 -0.47 0.431 -0.1302 -1.50 0.334 -0.1355 -2.52 0.221 -0.1344 -3.61 0.095 -0.1304 -4.63 -0.016 -0.1243 -5.68 -0.175 -0.1074 -6.61 -0.348 -0.0520 -7.49 -0.438 -0.0061 -8.47 -0.439 0.0095 Tabulated from data in file cl02346.dat & reduced using program C06.01 Average Reynolds #: 299607 Number of angles of attack: 59 alpha / Cl / Cm -9.02 -0.439 0.0178 -8.06 -0.463 0.0006 -6.85 -0.386 -0.0390 -6.13 -0.280 -0.0787 -5.05 -0.081 -0.1198 -4.04 0.051 -0.1267 -3.04 0.172 -0.1310 -1.98 0.289 -0.1319 -0.76 0.412 -0.1309 0.06 0.483 -0.1256 1.08 0.585 -0.1219 2.10 0.689 -0.1199 3.18 0.800 -0.1179 4.28 0.901 -0.1141 5.29 0.987 -0.1097 6.69 1.105 -0.1042 7.41 1.158 -0.1004 8.45 1.231 -0.0948 9.34 1.290 -0.0882 10.36 1.346 -0.0817 11.39 1.383 -0.0741 12.39 1.417 -0.0680 13.37 1.442 -0.0633 14.44 1.461 -0.0610 15.41 1.462 -0.0642 16.45 1.447 -0.0768 16.96 1.133 -0.2003 18.08 1.155 -0.2034 19.05 1.161 -0.2034 20.11 1.083 -0.2036 19.69 1.083 -0.2093 18.72 1.148 -0.2087 17.64 1.120 -0.2073 16.64 1.116 -0.1976 15.69 1.102 -0.1942 14.63 1.135 -0.1895 14.20 1.459 -0.0635 12.79 1.432 -0.0658 11.58 1.395 -0.0715 10.55 1.359 -0.0786 9.45 1.299 -0.0862 8.60 1.248 -0.0913 7.53 1.174 -0.0980 6.38 1.088 -0.1045 5.50 1.011 -0.1079 4.40 0.920 -0.1140 3.35 0.823 -0.1177 2.56 0.743 -0.1198 1.51 0.634 -0.1215 0.27 0.509 -0.1259 -0.50 0.447 -0.1314 -1.55 0.339 -0.1339 -2.49 0.239 -0.1346 -3.63 0.106 -0.1321 -4.67 -0.027 -0.1249 -5.61 -0.175 -0.1087 -6.82 -0.388 -0.0411 -7.62 -0.454 -0.0089 -8.56 -0.470 0.0111 Tabulated from data in file pg02648.dat & reduced using program C06.01 Average Reynolds #: 299855 Number of angles of attack: 59 alpha / Cl / Cm -8.93 -0.451 0.0159 -7.98 -0.451 0.0089 -6.90 -0.400 -0.0281 -5.92 -0.254 -0.0880 -5.05 -0.085 -0.1200 -4.05 0.047 -0.1270 -3.05 0.170 -0.1325 -2.02 0.285 -0.1337 -0.94 0.393 -0.1310 0.06 0.493 -0.1290 1.07 0.589 -0.1245 2.26 0.702 -0.1197 3.16 0.777 -0.1146 4.21 0.847 -0.1073 5.28 0.937 -0.1032 6.47 1.042 -0.0997 7.39 1.122 -0.0959 8.52 1.209 -0.0914 9.50 1.277 -0.0858 10.33 1.323 -0.0801 11.34 1.365 -0.0728 12.40 1.399 -0.0667 13.58 1.421 -0.0629 14.39 1.416 -0.0643 15.37 1.430 -0.0664 15.82 1.112 -0.1911 17.04 1.043 -0.1877 18.11 1.066 -0.1929 19.05 1.084 -0.2006 20.11 1.101 -0.2067 19.65 1.110 -0.2094 18.69 1.098 -0.1969 17.56 1.054 -0.1988 16.62 1.014 -0.1897 15.78 1.093 -0.1924 14.76 1.141 -0.1849 14.34 1.427 -0.0647 12.76 1.402 -0.0645 11.73 1.380 -0.0692 10.56 1.335 -0.0768 9.73 1.292 -0.0827 8.74 1.225 -0.0884 7.59 1.143 -0.0941 6.10 1.015 -0.1002 5.59 0.970 -0.1017 4.41 0.865 -0.1056 3.30 0.790 -0.1137 2.47 0.724 -0.1188 1.56 0.639 -0.1222 0.58 0.546 -0.1276 -0.51 0.445 -0.1307 -1.52 0.338 -0.1339 -2.52 0.232 -0.1344 -3.55 0.111 -0.1319 -4.67 -0.029 -0.1246 -5.66 -0.193 -0.1058 -6.62 -0.368 -0.0427 -7.51 -0.448 -0.0014 -8.38 -0.448 0.0124 Tabulated from data in file pg02650.dat & reduced using program C06.01 Average Reynolds #: 300061 Number of angles of attack: 59 alpha / Cl / Cm -8.99 -0.447 0.0151 -7.94 -0.455 0.0073 -6.97 -0.405 -0.0200 -6.09 -0.276 -0.0787 -4.99 -0.072 -0.1195 -4.08 0.047 -0.1268 -3.02 0.179 -0.1317 -1.97 0.293 -0.1316 -1.00 0.391 -0.1285 0.05 0.488 -0.1246 1.15 0.578 -0.1164 2.11 0.656 -0.1120 3.19 0.751 -0.1079 4.24 0.848 -0.1054 5.37 0.945 -0.1010 6.36 1.027 -0.0968 7.47 1.116 -0.0924 8.73 1.203 -0.0863 9.30 1.244 -0.0824 10.35 1.298 -0.0754 11.38 1.333 -0.0692 12.43 1.364 -0.0646 13.51 1.381 -0.0663 14.39 1.380 -0.0743 15.38 1.368 -0.0881 16.04 1.195 -0.1778 17.17 1.230 -0.1847 18.03 1.064 -0.1984 19.10 1.107 -0.2056 20.07 1.146 -0.2160 19.70 1.119 -0.2091 18.73 1.072 -0.2027 17.64 1.054 -0.1905 16.69 1.215 -0.1803 15.76 1.177 -0.1787 14.71 1.215 -0.1717 13.79 1.387 -0.0692 12.78 1.373 -0.0638 11.85 1.352 -0.0663 10.79 1.317 -0.0720 9.64 1.262 -0.0792 8.61 1.201 -0.0855 7.50 1.122 -0.0916 6.17 1.017 -0.0977 5.44 0.953 -0.1000 4.39 0.861 -0.1047 3.41 0.772 -0.1074 2.38 0.682 -0.1112 1.56 0.611 -0.1150 0.54 0.531 -0.1220 -0.48 0.447 -0.1281 -1.52 0.341 -0.1322 -2.60 0.228 -0.1337 -3.60 0.112 -0.1311 -4.61 -0.019 -0.1244 -5.81 -0.218 -0.0982 -6.67 -0.374 -0.0398 -7.52 -0.447 -0.0021 -8.41 -0.444 0.0123 Tabulated from data in file pg02652.dat & reduced using program C06.01 Average Reynolds #: 299764 Number of angles of attack: 59 alpha / Cl / Cm -8.97 -0.422 0.0168 -7.90 -0.429 0.0055 -6.91 -0.394 -0.0285 -6.04 -0.265 -0.0810 -5.02 -0.071 -0.1189 -3.93 0.072 -0.1273 -3.06 0.172 -0.1296 -2.01 0.281 -0.1262 -0.97 0.375 -0.1201 0.10 0.460 -0.1148 1.14 0.557 -0.1117 2.10 0.640 -0.1092 3.20 0.742 -0.1063 4.30 0.842 -0.1031 5.29 0.928 -0.0999 6.37 1.019 -0.0962 7.54 1.102 -0.0899 8.51 1.164 -0.0846 9.51 1.219 -0.0784 10.42 1.259 -0.0731 11.40 1.294 -0.0684 12.43 1.319 -0.0659 13.58 1.330 -0.0707 14.49 1.340 -0.0802 15.44 1.337 -0.0906 16.01 1.169 -0.1812 17.07 1.169 -0.1900 18.09 1.108 -0.1951 19.05 1.110 -0.2058 20.08 1.131 -0.2211 19.64 1.129 -0.2129 18.57 1.112 -0.2009 17.67 1.133 -0.1936 16.70 1.143 -0.1863 15.71 1.083 -0.1867 14.93 1.342 -0.1368 13.97 1.338 -0.0753 12.79 1.328 -0.0655 11.81 1.303 -0.0668 10.74 1.273 -0.0706 9.70 1.231 -0.0761 8.62 1.174 -0.0832 7.61 1.109 -0.0888 6.52 1.036 -0.0949 5.40 0.940 -0.0995 4.39 0.850 -0.1027 3.24 0.747 -0.1064 2.44 0.673 -0.1085 1.43 0.579 -0.1112 0.50 0.497 -0.1149 -0.50 0.416 -0.1187 -1.45 0.333 -0.1248 -2.49 0.234 -0.1297 -3.57 0.117 -0.1309 -4.57 -0.016 -0.1235 -5.59 -0.168 -0.1090 -6.70 -0.366 -0.0402 -7.55 -0.437 -0.0014 -8.53 -0.446 0.0115 Tabulated from data in file pg02654.dat & reduced using program C06.01 Average Reynolds #: 299892 Number of angles of attack: 59 alpha / Cl / Cm -8.85 -0.431 0.0149 -7.88 -0.443 0.0013 -6.83 -0.379 -0.0364 -6.03 -0.263 -0.0789 -5.06 -0.075 -0.1199 -4.05 0.065 -0.1292 -3.04 0.163 -0.1260 -2.00 0.245 -0.1177 -0.95 0.352 -0.1162 0.03 0.440 -0.1134 1.09 0.545 -0.1116 2.09 0.638 -0.1101 3.22 0.743 -0.1077 4.43 0.851 -0.1039 5.30 0.926 -0.1009 6.42 1.014 -0.0963 7.70 1.105 -0.0899 8.57 1.158 -0.0845 9.54 1.207 -0.0780 10.55 1.242 -0.0721 11.52 1.268 -0.0677 12.49 1.283 -0.0672 13.58 1.298 -0.0732 14.50 1.319 -0.0914 15.19 1.108 -0.1785 16.09 1.086 -0.1840 17.09 1.123 -0.1831 18.16 1.101 -0.1882 19.05 1.059 -0.2029 20.10 1.083 -0.2045 19.69 1.103 -0.2046 18.46 1.059 -0.1948 17.72 1.147 -0.1977 16.61 1.096 -0.1909 15.78 1.085 -0.1868 14.80 1.099 -0.1764 13.73 1.302 -0.0764 12.54 1.289 -0.0675 11.66 1.275 -0.0671 10.64 1.248 -0.0700 9.72 1.212 -0.0748 8.62 1.162 -0.0824 7.58 1.100 -0.0891 6.41 1.013 -0.0941 5.33 0.929 -0.0991 4.44 0.854 -0.1025 3.44 0.764 -0.1056 2.34 0.660 -0.1084 1.48 0.579 -0.1107 0.54 0.491 -0.1131 -0.59 0.386 -0.1159 -1.52 0.292 -0.1167 -2.46 0.206 -0.1212 -3.55 0.118 -0.1295 -4.57 -0.012 -0.1245 -5.61 -0.176 -0.1059 -6.77 -0.374 -0.0413 -7.75 -0.449 -0.0034 -8.45 -0.436 0.0116 Tabulated from data in file pg02551.dat & reduced using program C06.01 File sg6042t2.lft created using program C06.01 on Mon Feb 02 15:11:35 1998 :::::::::::::: SG6042T3.LFT :::::::::::::: Airfoil: SG6042 Builder: M. Allen Comment: LE tape 0.0065" thick from 5% l.s. to 5% u.s. Number of Reynolds #'s: 1 Average Reynolds #: 299791 Number of angles of attack: 59 alpha / Cl / Cm -8.93 -0.466 0.0094 -8.02 -0.467 0.0091 -6.87 -0.403 -0.0213 -5.97 -0.280 -0.0770 -5.01 -0.084 -0.1189 -4.02 0.049 -0.1267 -3.01 0.172 -0.1319 -2.03 0.283 -0.1336 -0.87 0.396 -0.1316 0.04 0.484 -0.1280 1.09 0.579 -0.1213 2.19 0.697 -0.1200 3.22 0.800 -0.1181 4.20 0.888 -0.1146 5.30 0.989 -0.1102 6.40 1.082 -0.1052 7.50 1.164 -0.0992 8.73 1.247 -0.0915 9.70 1.313 -0.0857 10.45 1.357 -0.0808 11.62 1.411 -0.0723 12.57 1.429 -0.0653 13.56 1.448 -0.0601 14.41 1.455 -0.0588 15.38 1.457 -0.0634 15.82 1.199 -0.1832 17.09 1.217 -0.1904 18.00 1.065 -0.1927 18.99 1.077 -0.2096 19.97 1.126 -0.2148 19.69 1.124 -0.2099 18.66 1.123 -0.2006 17.71 1.221 -0.1955 16.58 1.229 -0.1819 15.69 1.220 -0.1780 14.67 1.292 -0.1684 13.81 1.451 -0.0605 12.68 1.434 -0.0638 11.75 1.412 -0.0705 10.68 1.370 -0.0779 9.61 1.310 -0.0852 8.56 1.238 -0.0917 7.33 1.156 -0.0998 6.49 1.089 -0.1047 5.10 0.975 -0.1108 4.46 0.918 -0.1139 3.31 0.814 -0.1185 2.33 0.719 -0.1214 1.56 0.637 -0.1220 0.41 0.518 -0.1254 -0.50 0.440 -0.1299 -1.62 0.330 -0.1339 -2.53 0.235 -0.1345 -3.63 0.104 -0.1311 -4.73 -0.036 -0.1242 -5.81 -0.234 -0.0902 -6.59 -0.365 -0.0396 -7.63 -0.449 0.0036 -8.55 -0.445 0.0097 Tabulated from data in file pg02694.dat & reduced using program C06.01 File sg6042t3.lft created using program C06.01 on Mon Feb 02 15:11:35 1998 :::::::::::::: SG6043.LFT :::::::::::::: Airfoil: SG6043 Builder: M. Allen Comment: clean Number of Reynolds #'s: 6 Average Reynolds #: 99911 Number of angles of attack: 59 alpha / Cl / Cm -8.82 -0.313 0.0157 -7.96 -0.334 0.0187 -6.90 -0.383 0.0207 -5.82 -0.372 0.0173 -4.94 -0.359 -0.0022 -4.07 -0.247 -0.0451 -3.02 0.067 -0.1285 -1.95 0.196 -0.1427 -0.90 0.299 -0.1476 0.10 0.387 -0.1498 1.11 0.478 -0.1513 2.39 0.646 -0.1595 3.14 0.763 -0.1641 4.22 0.988 -0.1724 5.19 1.125 -0.1707 6.29 1.230 -0.1639 7.27 1.305 -0.1576 8.40 1.391 -0.1510 9.36 1.436 -0.1438 10.34 1.448 -0.1304 11.43 1.464 -0.1224 12.33 1.478 -0.1180 13.30 1.501 -0.1130 14.45 1.511 -0.1060 15.45 1.519 -0.1053 16.12 1.137 -0.2010 17.37 1.182 -0.2151 18.27 1.211 -0.2191 19.28 1.202 -0.2290 20.27 1.273 -0.2240 19.37 1.197 -0.2323 18.46 1.223 -0.2384 17.45 1.198 -0.2298 16.48 1.158 -0.2153 15.49 1.161 -0.2130 14.42 1.164 -0.2045 13.57 1.509 -0.1198 12.72 1.488 -0.1222 11.66 1.460 -0.1313 10.71 1.449 -0.1376 9.58 1.434 -0.1443 8.42 1.399 -0.1556 7.38 1.329 -0.1614 6.58 1.269 -0.1666 5.61 1.185 -0.1731 4.49 1.039 -0.1746 3.21 0.798 -0.1672 2.47 0.676 -0.1616 1.40 0.551 -0.1549 0.33 0.430 -0.1487 -0.64 0.374 -0.1551 -1.63 0.255 -0.1456 -2.64 0.144 -0.1362 -3.74 -0.111 -0.0863 -4.69 -0.342 -0.0154 -5.64 -0.359 0.0022 -6.63 -0.376 0.0160 -7.62 -0.366 0.0211 -8.80 -0.291 0.0116 Tabulated from data in file pg02384.dat & reduced using program C06.01 Average Reynolds #: 149958 Number of angles of attack: 59 alpha / Cl / Cm -8.99 -0.300 0.0203 -7.84 -0.357 0.0263 -7.00 -0.358 0.0244 -5.92 -0.357 0.0097 -4.95 -0.297 -0.0227 -3.92 -0.028 -0.1143 -2.90 0.172 -0.1454 -1.73 0.328 -0.1566 -0.72 0.471 -0.1673 0.32 0.594 -0.1696 1.31 0.744 -0.1756 2.23 0.866 -0.1791 3.41 1.003 -0.1773 4.32 1.092 -0.1732 5.35 1.191 -0.1682 6.37 1.278 -0.1622 7.60 1.374 -0.1533 8.42 1.426 -0.1463 9.47 1.467 -0.1342 10.50 1.483 -0.1214 11.48 1.517 -0.1121 12.51 1.535 -0.1033 13.39 1.548 -0.0964 14.44 1.555 -0.0915 15.40 1.551 -0.0923 16.39 1.535 -0.0977 17.13 1.147 -0.2201 18.63 1.131 -0.2267 19.35 1.142 -0.2230 20.31 1.186 -0.2259 18.98 1.177 -0.2296 18.14 1.149 -0.2331 17.15 1.128 -0.2242 16.17 1.145 -0.2210 15.24 1.167 -0.2143 14.50 1.559 -0.0949 13.69 1.554 -0.0975 12.71 1.546 -0.1041 11.68 1.522 -0.1124 10.55 1.491 -0.1224 9.58 1.467 -0.1334 8.40 1.423 -0.1467 7.55 1.373 -0.1533 6.44 1.291 -0.1611 5.22 1.182 -0.1677 4.39 1.104 -0.1716 3.43 1.008 -0.1755 2.26 0.872 -0.1784 1.25 0.738 -0.1739 0.18 0.577 -0.1687 -0.70 0.467 -0.1655 -1.78 0.329 -0.1550 -2.81 0.193 -0.1459 -3.86 -0.016 -0.1147 -4.71 -0.254 -0.0425 -5.66 -0.342 -0.0075 -6.63 -0.349 0.0120 -7.63 -0.342 0.0193 -8.66 -0.269 0.0115 Tabulated from data in file pg02501.dat & reduced using program C06.01 Average Reynolds #: 199819 Number of angles of attack: 59 alpha / Cl / Cm -8.74 -0.334 0.0100 -8.02 -0.333 0.0094 -7.00 -0.339 -0.0037 -5.95 -0.281 -0.0274 -4.92 -0.134 -0.0850 -4.00 0.131 -0.1566 -3.08 0.277 -0.1698 -1.76 0.464 -0.1809 -0.98 0.567 -0.1868 0.14 0.679 -0.1825 1.58 0.839 -0.1819 2.27 0.915 -0.1812 3.30 1.019 -0.1776 4.50 1.137 -0.1725 5.37 1.224 -0.1694 6.34 1.304 -0.1639 7.52 1.389 -0.1550 8.33 1.430 -0.1472 9.43 1.475 -0.1347 10.40 1.498 -0.1226 11.37 1.531 -0.1136 12.37 1.555 -0.1061 13.39 1.575 -0.0980 14.39 1.583 -0.1062 15.47 1.592 -0.0997 16.47 1.584 -0.0962 17.39 1.582 -0.0990 17.82 1.208 -0.2259 19.07 1.192 -0.2267 20.18 1.255 -0.2302 19.37 1.244 -0.2348 18.41 1.194 -0.2277 17.40 1.210 -0.2223 16.44 1.162 -0.2169 15.41 1.465 -0.1045 14.66 1.594 -0.1085 13.27 1.573 -0.1047 12.52 1.563 -0.1061 11.57 1.535 -0.1119 10.54 1.510 -0.1215 9.45 1.481 -0.1344 8.36 1.438 -0.1470 7.37 1.382 -0.1557 6.22 1.297 -0.1636 5.20 1.207 -0.1691 4.31 1.126 -0.1725 3.38 1.034 -0.1762 2.39 0.931 -0.1790 1.37 0.814 -0.1804 0.18 0.682 -0.1807 -0.64 0.613 -0.1857 -1.70 0.468 -0.1796 -2.78 0.318 -0.1721 -3.92 0.142 -0.1593 -4.69 -0.081 -0.1085 -5.70 -0.245 -0.0388 -6.63 -0.330 -0.0115 -7.65 -0.332 0.0039 -8.69 -0.309 0.0059 Tabulated from data in file pg02386.dat & reduced using program C06.01 Average Reynolds #: 299800 Number of angles of attack: 59 alpha / Cl / Cm -8.68 -0.291 -0.0013 -7.97 -0.292 -0.0158 -6.97 -0.217 -0.0408 -6.17 -0.134 -0.0765 -5.19 0.053 -0.1430 -4.13 0.270 -0.1860 -3.10 0.392 -0.1881 -2.06 0.511 -0.1900 -0.99 0.629 -0.1920 -0.01 0.727 -0.1892 1.06 0.834 -0.1846 2.07 0.941 -0.1835 3.10 1.042 -0.1811 4.25 1.159 -0.1784 5.07 1.232 -0.1745 6.23 1.328 -0.1671 7.25 1.399 -0.1586 8.33 1.456 -0.1478 9.39 1.504 -0.1368 10.33 1.530 -0.1264 11.45 1.570 -0.1160 12.51 1.596 -0.1073 13.60 1.621 -0.1013 14.61 1.642 -0.1002 15.74 1.653 -0.1019 16.66 1.646 -0.1044 17.47 1.649 -0.1071 18.56 1.625 -0.1168 19.32 1.603 -0.1195 19.91 1.288 -0.2544 19.60 1.215 -0.2419 18.60 1.203 -0.2361 17.57 1.173 -0.2237 16.50 1.225 -0.2217 16.24 1.654 -0.0957 14.64 1.643 -0.0944 13.61 1.619 -0.0976 12.52 1.600 -0.1024 11.32 1.569 -0.1121 10.32 1.534 -0.1225 9.69 1.512 -0.1288 8.57 1.471 -0.1416 7.64 1.426 -0.1513 6.54 1.352 -0.1605 5.53 1.270 -0.1671 4.57 1.183 -0.1723 3.57 1.085 -0.1758 2.52 0.979 -0.1784 1.48 0.873 -0.1798 0.47 0.767 -0.1825 -0.59 0.676 -0.1888 -1.69 0.554 -0.1889 -2.62 0.448 -0.1877 -3.66 0.330 -0.1860 -4.68 0.163 -0.1705 -5.66 -0.042 -0.1146 -6.69 -0.197 -0.0521 -7.67 -0.277 -0.0208 -8.84 -0.315 -0.0007 Tabulated from data in file pg02389.dat & reduced using program C06.01 Average Reynolds #: 399815 Number of angles of attack: 59 alpha / Cl / Cm -8.33 -0.297 -0.0141 -8.08 -0.275 -0.0216 -7.37 -0.210 -0.0464 -6.46 -0.100 -0.0918 -5.28 0.107 -0.1616 -4.14 0.301 -0.1875 -3.14 0.409 -0.1880 -2.07 0.528 -0.1887 -1.01 0.643 -0.1881 -0.07 0.740 -0.1877 0.94 0.836 -0.1814 1.99 0.947 -0.1803 3.08 1.057 -0.1773 4.09 1.153 -0.1729 5.16 1.248 -0.1671 6.16 1.332 -0.1606 7.28 1.408 -0.1508 8.23 1.461 -0.1413 9.39 1.512 -0.1295 10.40 1.550 -0.1192 11.41 1.582 -0.1115 12.51 1.613 -0.1043 13.37 1.633 -0.0995 14.63 1.663 -0.0955 15.51 1.665 -0.0959 16.34 1.677 -0.0986 17.31 1.658 -0.1036 18.34 1.627 -0.1082 19.29 1.615 -0.1165 20.31 1.587 -0.1266 19.57 1.611 -0.1279 18.54 1.638 -0.1153 17.44 1.655 -0.1064 16.40 1.682 -0.0998 15.36 1.672 -0.0935 14.36 1.651 -0.0931 13.13 1.633 -0.0988 12.38 1.613 -0.1029 11.56 1.593 -0.1086 10.50 1.549 -0.1170 9.54 1.515 -0.1265 8.45 1.469 -0.1382 7.51 1.419 -0.1476 6.55 1.361 -0.1564 5.61 1.291 -0.1636 4.51 1.195 -0.1705 3.40 1.089 -0.1751 2.25 0.976 -0.1785 1.44 0.891 -0.1805 0.46 0.790 -0.1838 -0.62 0.688 -0.1869 -1.69 0.565 -0.1862 -2.61 0.467 -0.1864 -3.60 0.356 -0.1854 -4.63 0.219 -0.1805 -5.66 0.028 -0.1348 -6.59 -0.114 -0.0835 -7.65 -0.229 -0.0365 -8.32 -0.298 -0.0117 Tabulated from data in file pg02392.dat & reduced using program C06.01 Average Reynolds #: 499253 Number of angles of attack: 53 alpha / Cl / Cm -6.39 -0.050 -0.1087 -5.22 0.145 -0.1710 -4.17 0.315 -0.1911 -3.16 0.429 -0.1920 -2.10 0.550 -0.1926 -1.08 0.659 -0.1930 -0.04 0.768 -0.1918 0.98 0.872 -0.1875 2.08 0.983 -0.1852 3.03 1.076 -0.1814 4.18 1.181 -0.1764 5.19 1.267 -0.1704 6.16 1.341 -0.1633 7.16 1.405 -0.1543 8.19 1.468 -0.1439 9.34 1.520 -0.1326 10.37 1.557 -0.1226 11.31 1.592 -0.1149 12.39 1.627 -0.1075 13.42 1.651 -0.1010 14.44 1.675 -0.0992 15.42 1.690 -0.1016 16.37 1.678 -0.1051 17.32 1.658 -0.1106 18.35 1.632 -0.1175 19.42 1.616 -0.1273 20.50 1.589 -0.1383 19.64 1.615 -0.1303 18.55 1.617 -0.1206 17.63 1.649 -0.1129 16.46 1.677 -0.1055 15.38 1.699 -0.0974 14.37 1.676 -0.0971 12.99 1.642 -0.1025 12.45 1.633 -0.1061 11.64 1.600 -0.1110 10.65 1.571 -0.1181 9.63 1.531 -0.1269 8.58 1.484 -0.1372 7.64 1.436 -0.1465 6.58 1.373 -0.1561 5.59 1.304 -0.1636 4.60 1.223 -0.1708 3.55 1.131 -0.1766 2.50 1.031 -0.1803 1.50 0.926 -0.1821 0.44 0.824 -0.1874 -0.59 0.725 -0.1904 -1.65 0.605 -0.1904 -2.61 0.500 -0.1903 -3.72 0.375 -0.1902 -4.68 0.252 -0.1877 -5.65 0.063 -0.1497 Tabulated from data in file pg02396.dat & reduced using program C06.01 File sg6043.lft created using program C06.01 on Mon Feb 02 15:11:35 1998 :::::::::::::: SG6043T.LFT :::::::::::::: Airfoil: SG6043 Builder: M. Allen Comment: Zigzag trip Type C (h = 0.023") @ 2% u.s. & 5% l.s. (Cm @ 500,000 is incorrect) Number of Reynolds #'s: 6 Average Reynolds #: 99939 Number of angles of attack: 59 alpha / Cl / Cm -9.07 -0.281 0.0158 -8.01 -0.336 0.0184 -7.01 -0.376 0.0224 -6.02 -0.378 0.0182 -5.01 -0.376 0.0039 -4.11 -0.278 -0.0393 -3.09 0.028 -0.1231 -2.08 0.178 -0.1398 -0.95 0.293 -0.1467 0.00 0.362 -0.1460 0.95 0.444 -0.1512 2.07 0.755 -0.1692 3.15 0.891 -0.1620 4.15 0.947 -0.1509 5.21 0.998 -0.1401 6.18 1.052 -0.1334 7.31 1.121 -0.1262 8.19 1.176 -0.1205 9.37 1.232 -0.1127 10.20 1.257 -0.1055 11.40 1.298 -0.0985 12.20 1.318 -0.0955 13.44 1.344 -0.0923 14.23 1.355 -0.0933 15.36 1.366 -0.0943 16.26 1.364 -0.0962 17.09 1.109 -0.2114 18.21 1.108 -0.2228 19.15 1.097 -0.2260 20.28 1.170 -0.2450 19.37 1.156 -0.2403 18.48 1.107 -0.2201 17.46 1.076 -0.2266 16.41 1.063 -0.2164 15.68 1.327 -0.1095 14.67 1.335 -0.1001 13.72 1.342 -0.1021 12.73 1.324 -0.1017 11.60 1.302 -0.1031 10.68 1.284 -0.1075 9.53 1.250 -0.1147 8.65 1.206 -0.1206 7.62 1.153 -0.1264 6.54 1.093 -0.1337 5.61 1.040 -0.1404 4.55 0.979 -0.1483 3.54 0.942 -0.1621 2.41 0.837 -0.1713 1.42 0.547 -0.1646 0.42 0.408 -0.1525 -0.78 0.329 -0.1540 -1.62 0.241 -0.1448 -2.66 0.133 -0.1373 -3.65 -0.084 -0.1067 -4.79 -0.361 -0.0151 -5.62 -0.416 0.0072 -6.70 -0.419 0.0159 -7.65 -0.395 0.0123 -8.70 -0.276 0.0002 Tabulated from data in file pg02535.dat & reduced using program C06.01 Average Reynolds #: 149866 Number of angles of attack: 59 alpha / Cl / Cm -9.08 -0.314 0.0105 -7.96 -0.369 0.0150 -7.09 -0.360 0.0163 -6.01 -0.368 0.0020 -4.95 -0.303 -0.0292 -4.02 -0.093 -0.0961 -2.98 0.154 -0.1481 -1.95 0.282 -0.1575 -0.84 0.435 -0.1678 0.13 0.642 -0.1802 1.25 0.762 -0.1710 2.25 0.832 -0.1626 3.29 0.900 -0.1541 4.20 0.959 -0.1475 5.26 1.032 -0.1408 6.20 1.094 -0.1346 7.22 1.163 -0.1249 8.25 1.226 -0.1191 9.42 1.275 -0.1111 10.39 1.304 -0.1045 11.34 1.323 -0.0988 12.32 1.352 -0.0969 13.22 1.354 -0.0954 14.36 1.366 -0.0984 15.50 1.378 -0.1026 16.43 1.371 -0.1076 17.34 1.361 -0.1143 18.13 1.151 -0.2236 19.24 1.127 -0.2210 20.28 1.190 -0.2373 19.11 1.163 -0.2329 18.16 1.189 -0.2306 17.22 1.138 -0.2331 16.64 1.382 -0.1155 15.61 1.388 -0.1092 14.73 1.372 -0.1058 13.72 1.381 -0.1020 12.68 1.345 -0.1011 11.71 1.334 -0.1024 10.70 1.319 -0.1069 9.57 1.284 -0.1137 8.49 1.240 -0.1210 7.68 1.198 -0.1262 6.58 1.127 -0.1350 5.34 1.038 -0.1451 4.34 0.972 -0.1491 3.53 0.915 -0.1541 2.46 0.845 -0.1619 1.38 0.773 -0.1708 0.40 0.682 -0.1799 -0.74 0.458 -0.1697 -1.77 0.312 -0.1600 -2.69 0.186 -0.1526 -3.78 -0.026 -0.1209 -4.74 -0.281 -0.0500 -5.67 -0.354 -0.0134 -6.62 -0.386 0.0046 -7.59 -0.360 0.0090 -8.58 -0.313 0.0097 Tabulated from data in file pg02536.dat & reduced using program C06.01 Average Reynolds #: 199880 Number of angles of attack: 59 alpha / Cl / Cm -9.03 -0.298 0.0077 -8.09 -0.325 0.0104 -7.08 -0.328 0.0009 -6.02 -0.289 -0.0181 -4.94 -0.165 -0.0735 -4.02 0.080 -0.1473 -3.09 0.259 -0.1694 -2.07 0.414 -0.1801 -0.97 0.567 -0.1824 0.01 0.666 -0.1746 1.23 0.758 -0.1655 2.25 0.835 -0.1593 3.23 0.911 -0.1535 4.67 1.022 -0.1456 5.39 1.076 -0.1413 6.33 1.142 -0.1357 7.51 1.212 -0.1270 8.37 1.254 -0.1205 9.40 1.294 -0.1125 10.42 1.330 -0.1062 11.36 1.352 -0.1025 12.46 1.373 -0.1007 13.27 1.393 -0.1012 14.41 1.394 -0.1055 15.47 1.374 -0.1098 16.41 1.395 -0.1148 17.42 1.385 -0.1276 18.06 1.158 -0.2246 19.07 1.212 -0.2266 20.06 1.214 -0.2506 19.54 1.179 -0.2312 18.54 1.162 -0.2268 17.50 1.191 -0.2246 16.89 1.364 -0.1244 15.60 1.379 -0.1130 14.68 1.394 -0.1086 13.63 1.391 -0.1021 12.57 1.371 -0.1019 11.64 1.360 -0.1027 10.63 1.336 -0.1061 9.57 1.302 -0.1119 8.61 1.265 -0.1192 7.53 1.218 -0.1283 6.44 1.154 -0.1359 5.37 1.078 -0.1424 4.37 1.003 -0.1482 3.12 0.904 -0.1546 2.31 0.844 -0.1594 1.30 0.768 -0.1654 0.33 0.694 -0.1725 -0.70 0.609 -0.1812 -1.78 0.461 -0.1831 -2.69 0.315 -0.1731 -3.92 0.113 -0.1540 -4.81 -0.137 -0.0821 -5.65 -0.264 -0.0365 -6.59 -0.301 -0.0052 -7.58 -0.321 0.0079 -8.61 -0.298 0.0068 Tabulated from data in file pg02538.dat & reduced using program C06.01 Average Reynolds #: 299852 Number of angles of attack: 59 alpha / Cl / Cm -9.12 -0.314 0.0013 -7.97 -0.284 -0.0120 -6.92 -0.232 -0.0403 -6.14 -0.158 -0.0686 -5.26 0.011 -0.1340 -4.15 0.253 -0.1861 -2.97 0.402 -0.1857 -2.10 0.475 -0.1792 -1.07 0.566 -0.1743 -0.01 0.656 -0.1696 0.97 0.745 -0.1653 2.15 0.846 -0.1601 3.03 0.921 -0.1565 4.05 1.005 -0.1507 5.14 1.091 -0.1447 6.20 1.161 -0.1377 7.11 1.218 -0.1306 8.20 1.278 -0.1229 9.16 1.317 -0.1160 10.29 1.356 -0.1094 11.33 1.383 -0.1047 12.53 1.405 -0.1035 13.34 1.421 -0.1066 14.36 1.418 -0.1113 15.25 1.393 -0.1160 16.19 1.405 -0.1258 17.17 1.382 -0.1351 17.76 1.222 -0.2235 18.89 1.181 -0.2288 20.01 1.170 -0.2386 19.43 1.174 -0.2408 18.54 1.168 -0.2366 17.58 1.265 -0.2233 16.93 1.369 -0.1362 15.26 1.399 -0.1179 14.37 1.421 -0.1114 13.25 1.408 -0.1035 12.32 1.385 -0.1019 10.98 1.364 -0.1056 10.21 1.349 -0.1095 9.16 1.310 -0.1148 8.26 1.272 -0.1205 7.28 1.225 -0.1278 6.44 1.174 -0.1343 5.45 1.109 -0.1403 4.44 1.031 -0.1460 3.44 0.953 -0.1517 2.53 0.878 -0.1559 1.38 0.778 -0.1603 0.48 0.701 -0.1647 -0.59 0.617 -0.1706 -1.61 0.518 -0.1750 -2.64 0.432 -0.1815 -3.66 0.335 -0.1885 -4.71 0.131 -0.1683 -5.71 -0.085 -0.0989 -6.91 -0.224 -0.0394 -7.81 -0.287 -0.0154 -8.69 -0.312 0.0015 Tabulated from data in file pg02539.dat & reduced using program C06.01 Average Reynolds #: 399687 Number of angles of attack: 47 alpha / Cl / Cm -7.02 -0.186 -0.0587 -6.28 -0.083 -0.0986 -5.22 0.086 -0.1543 -4.10 0.292 -0.1826 -3.01 0.389 -0.1781 -2.04 0.482 -0.1754 -1.04 0.574 -0.1715 -0.01 0.665 -0.1674 1.01 0.763 -0.1637 2.01 0.853 -0.1608 3.05 0.942 -0.1557 4.10 1.034 -0.1509 5.13 1.109 -0.1434 6.10 1.176 -0.1372 7.18 1.241 -0.1295 8.11 1.293 -0.1228 9.16 1.341 -0.1159 10.20 1.375 -0.1100 11.23 1.405 -0.1055 12.23 1.420 -0.1043 13.20 1.436 -0.1060 14.24 1.445 -0.1113 15.22 1.439 -0.1194 16.16 1.419 -0.1293 15.42 1.434 -0.1230 14.51 1.428 -0.1126 13.55 1.435 -0.1092 12.42 1.429 -0.1042 11.48 1.410 -0.1037 10.41 1.378 -0.1061 9.50 1.347 -0.1112 8.05 1.283 -0.1206 7.61 1.264 -0.1230 6.60 1.207 -0.1307 5.63 1.145 -0.1382 4.56 1.067 -0.1452 3.53 0.985 -0.1513 2.49 0.896 -0.1564 1.41 0.799 -0.1604 0.50 0.713 -0.1638 -0.59 0.616 -0.1667 -1.61 0.520 -0.1716 -2.65 0.420 -0.1746 -3.64 0.328 -0.1783 -4.70 0.207 -0.1783 -5.73 -0.001 -0.1300 -6.64 -0.134 -0.0776 Tabulated from data in file pg02542.dat & reduced using program C06.01 Average Reynolds #: 499358 Number of angles of attack: 43 alpha / Cl / Cm -5.25 0.039 -0.0533 -4.02 0.286 -0.0704 -2.97 0.390 -0.0710 -1.98 0.485 -0.0712 -0.96 0.582 -0.0709 0.04 0.675 -0.0707 1.06 0.778 -0.0704 2.11 0.874 -0.0702 3.13 0.962 -0.0695 4.17 1.052 -0.0685 5.18 1.131 -0.0672 6.28 1.204 -0.0648 7.24 1.259 -0.0627 8.24 1.302 -0.0604 9.28 1.344 -0.0585 10.31 1.375 -0.0568 11.31 1.402 -0.0557 12.32 1.423 -0.0561 13.28 1.427 -0.0571 14.26 1.434 -0.0595 15.38 1.415 -0.0639 16.17 1.372 -0.0679 15.72 1.387 -0.0652 14.50 1.429 -0.0607 12.95 1.433 -0.0570 12.52 1.421 -0.0562 11.21 1.401 -0.0560 10.48 1.378 -0.0567 9.40 1.349 -0.0584 8.62 1.317 -0.0597 7.43 1.265 -0.0622 6.49 1.212 -0.0644 5.64 1.155 -0.0657 4.59 1.080 -0.0676 3.57 0.999 -0.0689 2.59 0.919 -0.0700 1.61 0.829 -0.0705 0.45 0.719 -0.0708 -0.47 0.637 -0.0708 -1.50 0.534 -0.0711 -2.45 0.441 -0.0705 -3.51 0.340 -0.0707 -4.58 0.216 -0.0689 Tabulated from data in file pg02544.dat & reduced using program C06.01 File sg6043t.lft created using program C06.01 on Mon Feb 02 15:11:35 1998 :::::::::::::: TRNR60.LFT :::::::::::::: Airfoil: Trainer 60 Builder: J. Thomas Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 101700 Number of angles of attack: 49 alpha / Cl / Cm -6.16 -0.656 0.0128 -4.99 -0.533 -0.0051 -3.98 -0.425 -0.0104 -2.97 -0.344 -0.0065 -1.95 -0.247 -0.0027 -0.92 -0.143 0.0006 0.55 -0.008 0.0063 1.29 0.060 0.0091 2.30 0.156 0.0125 3.34 0.243 0.0169 4.39 0.347 0.0161 5.60 0.509 0.0062 6.35 0.582 0.0047 7.41 0.688 0.0035 8.43 0.788 0.0022 9.45 0.870 0.0017 10.46 0.951 0.0015 11.47 1.031 0.0014 12.48 1.094 0.0025 13.48 1.151 0.0041 14.47 1.185 0.0037 15.45 1.161 -0.0186 16.46 1.140 -0.0215 17.34 0.652 -0.0805 18.41 0.704 -0.0930 16.92 0.654 -0.0903 15.80 0.626 -0.0817 14.91 0.609 -0.0755 13.81 0.585 -0.0700 12.93 0.570 -0.0663 11.89 0.554 -0.0632 10.83 0.547 -0.0594 10.01 0.573 -0.0534 9.08 0.836 -0.0085 7.94 0.746 0.0010 6.95 0.650 0.0027 5.92 0.555 0.0046 4.87 0.423 0.0109 3.83 0.292 0.0164 2.80 0.213 0.0133 1.79 0.122 0.0113 0.77 0.026 0.0078 -0.23 -0.063 0.0047 -1.22 -0.156 0.0025 -2.22 -0.257 0.0000 -3.40 -0.367 -0.0040 -4.41 -0.461 -0.0065 -5.45 -0.578 0.0005 -6.47 -0.677 0.0058 Tabulated from data in file CL01047.DAT & reduced using program Q06.01L Average Reynolds #: 202500 Number of angles of attack: 53 alpha / Cl / Cm -6.13 -0.688 0.0052 -4.76 -0.560 0.0055 -3.76 -0.467 0.0071 -2.74 -0.360 0.0070 -1.71 -0.248 0.0064 -0.69 -0.137 0.0061 0.33 -0.029 0.0060 1.32 0.071 0.0066 2.32 0.170 0.0066 3.37 0.273 0.0072 4.40 0.376 0.0091 5.42 0.480 0.0102 6.37 0.588 0.0095 7.59 0.736 0.0051 8.54 0.834 0.0038 9.47 0.924 0.0029 10.41 1.012 0.0029 11.68 1.120 0.0038 12.59 1.170 0.0058 13.50 1.209 -0.0019 14.71 1.182 -0.0228 15.63 1.163 -0.0279 16.58 1.155 -0.0310 17.55 1.150 -0.0354 18.49 1.054 -0.0461 19.75 1.043 -0.0447 20.39 0.734 -0.1026 18.38 0.716 -0.1012 17.71 0.739 -0.1009 17.02 1.157 -0.0362 15.88 1.163 -0.0323 15.06 1.184 -0.0278 14.02 1.199 -0.0124 13.04 1.197 0.0032 12.05 1.153 0.0024 11.03 1.075 0.0016 10.02 0.980 0.0014 8.98 0.880 0.0018 7.91 0.772 0.0029 6.83 0.656 0.0053 5.90 0.530 0.0088 4.82 0.415 0.0093 3.70 0.308 0.0080 2.82 0.221 0.0076 1.62 0.105 0.0082 0.73 0.014 0.0082 -0.40 -0.104 0.0081 -1.26 -0.198 0.0089 -2.38 -0.317 0.0093 -3.51 -0.435 0.0097 -4.38 -0.522 0.0086 -5.55 -0.637 0.0065 -6.48 -0.726 0.0056 Tabulated from data in file CL01049.DAT & reduced using program Q06.01L Average Reynolds #: 303500 Number of angles of attack: 50 alpha / Cl / Cm -4.59 -0.571 0.0094 -3.88 -0.496 0.0092 -2.80 -0.377 0.0088 -1.72 -0.258 0.0077 -0.68 -0.138 0.0066 0.39 -0.021 0.0064 1.45 0.097 0.0062 2.53 0.207 0.0061 3.32 0.318 0.0061 4.29 0.422 0.0063 5.60 0.552 0.0090 6.50 0.648 0.0089 7.40 0.755 0.0053 8.29 0.853 0.0033 9.46 0.976 0.0017 10.60 1.094 0.0010 11.73 1.179 0.0031 12.57 1.205 -0.0013 13.65 1.214 -0.0164 14.51 1.214 -0.0208 15.70 1.173 -0.0304 16.64 1.178 -0.0365 17.55 1.071 -0.0495 18.57 1.048 -0.0507 19.57 1.024 -0.0505 20.55 1.051 -0.0569 18.73 1.035 -0.0530 17.82 1.067 -0.0541 16.98 1.174 -0.0399 15.61 1.174 -0.0323 15.02 1.167 -0.0301 13.94 1.186 -0.0267 13.00 1.204 -0.0111 11.90 1.187 0.0042 10.96 1.123 0.0029 10.06 1.037 0.0028 8.89 0.918 0.0036 7.92 0.813 0.0044 6.90 0.694 0.0075 5.86 0.577 0.0088 4.77 0.470 0.0066 3.67 0.354 0.0056 2.99 0.261 0.0056 1.61 0.110 0.0067 0.73 0.014 0.0069 -0.46 -0.117 0.0077 -1.35 -0.216 0.0089 -2.51 -0.347 0.0102 -3.39 -0.445 0.0107 -4.58 -0.573 0.0109 Tabulated from data in file CL01051.DAT & reduced using program Q06.01L Average Reynolds #: 405000 Number of angles of attack: 53 alpha / Cl / Cm -6.14 -0.720 0.0104 -4.56 -0.568 0.0104 -3.78 -0.497 0.0102 -2.62 -0.364 0.0094 -1.86 -0.276 0.0090 -0.72 -0.144 0.0077 0.47 -0.011 0.0073 1.23 0.072 0.0071 2.47 0.236 0.0066 3.51 0.353 0.0061 4.53 0.466 0.0057 5.49 0.566 0.0061 6.45 0.667 0.0063 7.67 0.802 0.0055 8.52 0.906 0.0019 9.69 1.030 0.0004 10.55 1.114 0.0005 11.67 1.187 0.0021 12.65 1.185 -0.0143 13.80 1.156 -0.0264 14.79 1.150 -0.0290 15.51 1.149 -0.0314 16.86 1.155 -0.0412 17.51 1.037 -0.0547 18.48 1.017 -0.0556 19.75 1.023 -0.0569 20.70 1.025 -0.0613 18.80 1.007 -0.0547 17.82 1.033 -0.0541 16.92 1.167 -0.0446 15.82 1.151 -0.0349 15.02 1.151 -0.0313 14.01 1.152 -0.0270 13.04 1.166 -0.0217 12.01 1.190 -0.0007 11.11 1.153 0.0041 9.93 1.049 0.0032 8.87 0.939 0.0034 7.98 0.835 0.0058 6.88 0.708 0.0082 5.92 0.609 0.0070 4.92 0.504 0.0061 3.88 0.391 0.0057 2.81 0.271 0.0061 1.87 0.138 0.0071 0.67 0.007 0.0076 -0.29 -0.101 0.0084 -1.50 -0.240 0.0093 -2.42 -0.345 0.0105 -3.36 -0.454 0.0112 -4.35 -0.557 0.0118 -5.38 -0.650 0.0114 -6.48 -0.760 0.0106 Tabulated from data in file AB01054.DAT & reduced using program Q06.01L Average Reynolds #: 506800 Number of angles of attack: 53 alpha / Cl / Cm -6.08 -0.766 0.0055 -4.62 -0.613 0.0056 -3.69 -0.513 0.0045 -2.64 -0.390 0.0049 -1.59 -0.271 0.0040 -0.60 -0.155 0.0036 0.34 -0.052 0.0029 1.70 0.106 0.0028 2.23 0.163 0.0022 3.55 0.309 0.0004 4.41 0.401 -0.0009 5.60 0.530 -0.0019 6.40 0.607 -0.0025 7.46 0.722 -0.0013 8.42 0.826 -0.0010 9.38 0.938 -0.0041 10.57 1.059 -0.0070 11.69 1.139 -0.0059 12.41 1.160 -0.0150 13.63 1.135 -0.0330 14.72 1.125 -0.0368 15.88 1.135 -0.0422 16.59 1.136 -0.0471 17.73 1.104 -0.0556 18.11 1.012 -0.0615 19.48 0.999 -0.0652 20.41 0.996 -0.0689 18.68 0.990 -0.0636 17.88 1.066 -0.0585 16.83 1.138 -0.0515 16.04 1.136 -0.0452 14.76 1.122 -0.0385 14.01 1.133 -0.0357 12.99 1.147 -0.0267 12.10 1.165 -0.0059 11.09 1.115 -0.0016 10.07 1.015 -0.0038 9.06 0.904 0.0007 7.92 0.773 0.0022 6.92 0.671 0.0019 5.76 0.556 0.0019 4.69 0.442 0.0024 3.84 0.349 0.0028 2.65 0.216 0.0037 1.65 0.107 0.0045 0.64 -0.009 0.0052 -0.48 -0.141 0.0061 -1.59 -0.263 0.0068 -2.35 -0.352 0.0070 -3.51 -0.487 0.0079 -4.82 -0.626 0.0095 -5.73 -0.730 0.0089 -6.77 -0.832 0.0087 Tabulated from data in file CL02073.DAT & reduced using program Q06.01L File TRNR60.LFT created on 10-24-1997 at 19:34:42 using program FORMAT :::::::::::::: ULTIMATE.LFT :::::::::::::: Airfoil: CG Ultimate Builder: M. Levoe Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 101100 Number of angles of attack: 49 alpha / Cl / Cm -5.83 -0.635 -0.0019 -4.59 -0.533 0.0040 -3.73 -0.467 0.0091 -2.50 -0.380 0.0193 -1.65 -0.317 0.0260 -0.47 -0.188 0.0246 0.70 0.028 -0.0011 1.53 0.194 -0.0209 2.71 0.319 -0.0259 3.53 0.376 -0.0245 4.74 0.468 -0.0153 5.57 0.535 -0.0099 6.82 0.640 -0.0047 7.65 0.683 0.0011 8.84 0.752 0.0080 9.62 0.802 0.0123 10.82 0.859 0.0170 11.94 0.853 -0.0108 12.72 0.854 -0.0396 13.85 0.766 -0.0658 14.64 0.754 -0.0708 15.85 0.697 -0.0685 16.69 0.725 -0.0737 18.00 0.765 -0.0842 18.91 0.778 -0.0873 16.96 0.712 -0.0820 16.10 0.710 -0.0804 14.97 0.711 -0.0757 13.83 0.745 -0.0727 13.04 0.777 -0.0676 11.93 0.878 -0.0062 11.15 0.864 0.0117 10.11 0.826 0.0096 9.05 0.765 0.0058 7.99 0.702 0.0011 6.91 0.646 -0.0059 6.12 0.584 -0.0092 5.02 0.500 -0.0164 3.92 0.414 -0.0235 2.80 0.336 -0.0307 2.01 0.272 -0.0335 0.85 0.062 -0.0118 -0.24 -0.141 0.0150 -1.34 -0.278 0.0232 -2.39 -0.361 0.0182 -3.47 -0.437 0.0094 -4.29 -0.502 0.0050 -5.39 -0.593 0.0009 -6.51 -0.670 -0.0037 Tabulated from data in file AB01670.DAT & reduced using program Q06.01L Average Reynolds #: 202200 Number of angles of attack: 49 alpha / Cl / Cm -5.84 -0.650 -0.0019 -4.57 -0.558 0.0032 -3.74 -0.489 0.0059 -2.51 -0.364 0.0070 -1.68 -0.234 -0.0016 -0.40 -0.058 -0.0094 0.44 0.017 -0.0058 1.66 0.125 -0.0005 2.53 0.222 -0.0016 3.80 0.392 -0.0113 4.64 0.483 -0.0125 5.85 0.585 -0.0081 6.65 0.638 -0.0031 7.68 0.707 0.0037 8.80 0.782 0.0092 9.59 0.829 0.0130 10.70 0.882 0.0176 11.74 0.900 -0.0093 12.79 0.845 -0.0601 13.61 0.784 -0.0762 14.85 0.731 -0.0815 15.74 0.730 -0.0826 16.67 0.721 -0.0840 17.60 0.731 -0.0861 18.90 0.748 -0.0873 16.74 0.712 -0.0840 15.86 0.716 -0.0831 14.99 0.730 -0.0835 13.76 0.747 -0.0806 12.93 0.838 -0.0661 11.90 0.903 -0.0241 11.19 0.918 0.0128 9.92 0.844 0.0106 8.93 0.789 0.0058 7.90 0.721 0.0011 6.88 0.654 -0.0056 5.81 0.579 -0.0120 4.98 0.512 -0.0152 3.80 0.395 -0.0147 2.95 0.277 -0.0075 1.86 0.142 -0.0023 0.72 0.039 -0.0055 -0.05 -0.029 -0.0093 -1.16 -0.154 -0.0078 -2.25 -0.324 0.0050 -3.37 -0.451 0.0076 -4.48 -0.552 0.0045 -5.33 -0.618 0.0014 -6.54 -0.687 -0.0054 Tabulated from data in file AB01673.DAT & reduced using program Q06.01L Average Reynolds #: 303300 Number of angles of attack: 49 alpha / Cl / Cm -5.88 -0.655 -0.0026 -4.47 -0.554 0.0035 -3.56 -0.451 0.0024 -2.68 -0.327 -0.0038 -1.36 -0.153 -0.0116 -0.47 -0.062 -0.0100 0.44 0.019 -0.0059 1.80 0.137 -0.0007 2.67 0.224 0.0006 3.71 0.378 -0.0042 4.55 0.490 -0.0093 5.82 0.609 -0.0078 6.63 0.658 -0.0024 7.79 0.739 0.0030 8.89 0.816 0.0079 9.62 0.860 0.0118 10.68 0.923 0.0155 11.71 0.935 -0.0015 12.90 0.887 -0.0555 13.67 0.834 -0.0740 14.85 0.775 -0.0836 15.67 0.739 -0.0830 16.89 0.742 -0.0847 17.71 0.757 -0.0873 18.92 0.778 -0.0894 16.76 0.754 -0.0852 15.83 0.754 -0.0843 14.94 0.767 -0.0831 14.10 0.830 -0.0814 12.95 0.900 -0.0552 11.99 0.943 -0.0149 11.01 0.945 0.0142 10.02 0.879 0.0129 9.03 0.823 0.0081 8.00 0.751 0.0033 6.95 0.678 -0.0019 5.84 0.609 -0.0085 5.04 0.544 -0.0112 3.98 0.411 -0.0060 3.05 0.272 -0.0007 1.98 0.154 -0.0004 0.84 0.053 -0.0047 -0.37 -0.054 -0.0105 -1.20 -0.137 -0.0125 -2.34 -0.288 -0.0067 -3.49 -0.452 0.0028 -4.35 -0.548 0.0050 -5.55 -0.637 0.0004 -6.50 -0.697 -0.0049 Tabulated from data in file AB01675.DAT & reduced using program Q06.01L Average Reynolds #: 404100 Number of angles of attack: 49 alpha / Cl / Cm -5.84 -0.661 -0.0043 -4.56 -0.556 -0.0010 -3.69 -0.445 -0.0053 -2.45 -0.283 -0.0112 -1.47 -0.170 -0.0122 -0.56 -0.078 -0.0101 0.81 0.052 -0.0060 1.66 0.135 -0.0037 2.79 0.266 -0.0008 3.62 0.358 -0.0019 4.79 0.498 -0.0058 5.54 0.584 -0.0085 6.92 0.684 -0.0024 7.78 0.746 0.0019 8.60 0.805 0.0055 10.15 0.898 0.0132 10.57 0.922 0.0145 11.64 0.940 -0.0047 12.58 0.925 -0.0449 13.63 0.883 -0.0724 14.68 0.805 -0.0823 15.73 0.766 -0.0845 16.78 0.769 -0.0864 17.62 0.889 -0.1140 18.73 0.924 -0.1173 16.62 0.796 -0.0920 15.77 0.778 -0.0865 14.85 0.805 -0.0846 14.03 0.863 -0.0792 12.95 0.928 -0.0551 11.98 0.947 -0.0156 10.93 0.958 0.0178 10.05 0.904 0.0163 9.12 0.842 0.0118 8.09 0.772 0.0072 7.03 0.694 0.0014 5.93 0.615 -0.0046 4.79 0.499 -0.0048 3.99 0.400 -0.0018 2.85 0.272 -0.0008 1.97 0.180 -0.0026 0.87 0.053 -0.0054 -0.18 -0.046 -0.0076 -1.48 -0.179 -0.0106 -2.49 -0.297 -0.0094 -3.53 -0.432 -0.0042 -4.53 -0.563 0.0021 -5.53 -0.646 -0.0002 -6.78 -0.716 -0.0072 Tabulated from data in file CL01677.DAT & reduced using program Q06.01L Average Reynolds #: 505400 Number of angles of attack: 49 alpha / Cl / Cm -5.87 -0.655 -0.0039 -4.49 -0.514 -0.0057 -3.73 -0.416 -0.0100 -2.62 -0.284 -0.0118 -1.48 -0.163 -0.0107 -0.50 -0.065 -0.0086 0.50 0.038 -0.0073 1.88 0.178 -0.0050 2.76 0.269 -0.0045 3.55 0.351 -0.0039 4.73 0.478 -0.0059 5.52 0.565 -0.0082 6.68 0.661 -0.0061 7.79 0.747 -0.0010 8.82 0.824 0.0030 9.82 0.883 0.0076 10.75 0.928 0.0119 11.73 0.946 -0.0038 12.24 0.954 -0.0251 13.56 0.897 -0.0710 14.52 0.832 -0.0817 15.50 0.832 -0.0905 16.25 0.883 -0.0956 17.01 0.924 -0.1231 18.36 0.982 -0.1324 17.04 0.937 -0.1134 15.63 0.845 -0.0934 14.89 0.796 -0.0855 14.13 0.867 -0.0778 13.24 0.914 -0.0630 12.45 0.957 -0.0336 11.18 0.970 0.0188 10.22 0.915 0.0171 9.15 0.863 0.0124 8.16 0.793 0.0079 7.00 0.707 0.0031 6.02 0.631 -0.0014 4.97 0.514 -0.0008 3.88 0.392 0.0010 2.68 0.266 -0.0008 1.84 0.181 -0.0025 0.51 0.040 -0.0041 -0.53 -0.069 -0.0064 -1.52 -0.168 -0.0072 -2.67 -0.291 -0.0080 -3.32 -0.370 -0.0072 -4.35 -0.500 -0.0017 -5.44 -0.623 0.0021 -6.63 -0.707 -0.0032 Tabulated from data in file CL01730.DAT & reduced using program Q06.01L File ULTIMATE.LFT created on 10-24-1997 at 19:34:42 using program FORMAT :::::::::::::: US1000.LFT :::::::::::::: Airfoil: Ultra-Sport 1000 Builder: D. Brengman Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 101800 Number of angles of attack: 49 alpha / Cl / Cm -6.02 -0.665 0.0066 -4.80 -0.587 0.0101 -3.60 -0.407 -0.0092 -2.75 -0.274 -0.0197 -1.56 -0.157 -0.0177 -0.78 -0.091 -0.0125 0.41 0.009 -0.0048 1.60 0.107 0.0010 2.37 0.162 0.0055 3.60 0.250 0.0126 4.40 0.336 0.0096 5.72 0.533 -0.0108 6.51 0.594 -0.0129 7.78 0.668 -0.0078 8.53 0.729 -0.0051 9.74 0.837 -0.0033 10.57 0.898 -0.0018 11.80 0.929 0.0021 12.59 0.909 -0.0034 13.75 0.884 -0.0110 14.51 0.865 -0.0168 15.71 0.857 -0.0215 16.51 0.861 -0.0240 17.73 0.858 -0.0267 18.52 0.852 -0.0318 16.80 0.858 -0.0271 16.08 0.867 -0.0270 15.03 0.861 -0.0235 13.99 0.853 -0.0143 12.98 0.881 -0.0117 12.00 0.913 -0.0047 11.02 0.910 -0.0046 10.03 0.849 -0.0066 9.05 0.772 -0.0086 8.06 0.679 -0.0089 7.05 0.609 -0.0122 5.98 0.555 -0.0173 4.93 0.416 -0.0046 3.89 0.272 0.0086 2.88 0.193 0.0061 1.87 0.122 0.0016 0.88 0.048 -0.0040 -0.12 -0.040 -0.0090 -1.42 -0.149 -0.0178 -2.12 -0.206 -0.0239 -3.47 -0.379 -0.0152 -4.50 -0.553 0.0039 -5.54 -0.645 0.0111 -6.32 -0.690 0.0079 Tabulated from data in file CL01679.DAT & reduced using program Q06.01L Average Reynolds #: 202800 Number of angles of attack: 49 alpha / Cl / Cm -5.87 -0.620 -0.0057 -4.78 -0.475 -0.0142 -3.68 -0.366 -0.0138 -2.66 -0.276 -0.0110 -1.58 -0.173 -0.0097 -0.59 -0.080 -0.0086 0.39 0.010 -0.0072 1.45 0.113 -0.0060 2.53 0.217 -0.0051 3.60 0.320 -0.0043 4.61 0.406 -0.0009 5.62 0.501 -0.0001 6.63 0.607 -0.0009 7.62 0.748 -0.0110 8.58 0.809 -0.0075 9.54 0.867 -0.0046 10.90 0.898 -0.0043 11.82 0.897 -0.0103 12.79 0.893 -0.0168 13.70 0.901 -0.0216 14.63 0.885 -0.0290 15.68 0.879 -0.0350 16.67 0.865 -0.0371 17.63 0.860 -0.0429 18.70 0.866 -0.0483 16.89 0.868 -0.0401 16.01 0.872 -0.0369 15.04 0.878 -0.0337 13.74 0.901 -0.0242 12.84 0.896 -0.0188 12.03 0.895 -0.0139 10.83 0.897 -0.0056 10.02 0.883 -0.0051 8.83 0.826 -0.0098 7.99 0.773 -0.0128 6.71 0.616 -0.0045 5.87 0.525 -0.0033 4.57 0.403 -0.0044 3.68 0.328 -0.0068 2.81 0.247 -0.0072 1.92 0.162 -0.0075 0.67 0.040 -0.0081 -0.20 -0.042 -0.0089 -1.43 -0.155 -0.0093 -2.37 -0.247 -0.0103 -3.27 -0.327 -0.0123 -4.60 -0.454 -0.0143 -5.54 -0.571 -0.0098 -6.55 -0.716 0.0021 Tabulated from data in file CL01681.DAT & reduced using program Q06.01L Average Reynolds #: 304200 Number of angles of attack: 49 alpha / Cl / Cm -5.78 -0.603 -0.0101 -4.62 -0.491 -0.0091 -3.53 -0.388 -0.0079 -2.47 -0.280 -0.0075 -1.42 -0.171 -0.0077 -0.32 -0.056 -0.0078 0.72 0.049 -0.0075 1.71 0.151 -0.0075 2.74 0.256 -0.0078 3.80 0.360 -0.0079 4.77 0.455 -0.0074 5.75 0.548 -0.0060 6.73 0.635 -0.0032 7.69 0.739 -0.0058 8.63 0.822 -0.0071 9.55 0.869 -0.0037 10.85 0.893 -0.0061 11.69 0.894 -0.0146 12.57 0.894 -0.0210 13.89 0.886 -0.0338 14.88 0.875 -0.0375 15.85 0.875 -0.0409 16.90 0.863 -0.0449 17.90 0.863 -0.0498 18.98 0.866 -0.0560 16.68 0.864 -0.0448 16.11 0.870 -0.0430 14.76 0.877 -0.0391 13.90 0.886 -0.0335 13.01 0.903 -0.0250 11.78 0.894 -0.0157 10.97 0.897 -0.0087 9.82 0.877 -0.0035 9.03 0.844 -0.0067 7.71 0.738 -0.0066 6.89 0.646 -0.0038 5.62 0.533 -0.0072 4.75 0.454 -0.0084 3.82 0.361 -0.0090 2.92 0.272 -0.0090 1.61 0.139 -0.0084 0.72 0.049 -0.0080 -0.23 -0.048 -0.0080 -1.55 -0.183 -0.0078 -2.45 -0.275 -0.0077 -3.40 -0.370 -0.0080 -4.35 -0.465 -0.0088 -5.40 -0.565 -0.0102 -6.41 -0.646 -0.0077 Tabulated from data in file CL01683.DAT & reduced using program Q06.01L Average Reynolds #: 406000 Number of angles of attack: 49 alpha / Cl / Cm -5.98 -0.643 -0.0086 -4.16 -0.465 -0.0075 -3.51 -0.398 -0.0074 -2.39 -0.279 -0.0074 -1.29 -0.162 -0.0076 -0.64 -0.093 -0.0078 0.45 0.022 -0.0081 1.54 0.134 -0.0085 2.55 0.243 -0.0091 3.70 0.361 -0.0098 4.72 0.466 -0.0105 5.76 0.569 -0.0104 6.69 0.658 -0.0095 7.62 0.734 -0.0066 8.53 0.808 -0.0062 9.83 0.865 -0.0022 10.64 0.881 -0.0068 11.89 0.883 -0.0193 12.75 0.890 -0.0266 13.69 0.874 -0.0364 14.63 0.868 -0.0412 15.70 0.857 -0.0464 16.73 0.855 -0.0493 17.83 0.859 -0.0534 18.92 0.882 -0.0604 16.48 0.847 -0.0485 15.93 0.860 -0.0462 14.98 0.860 -0.0432 13.62 0.885 -0.0365 13.10 0.891 -0.0306 11.92 0.884 -0.0210 10.77 0.882 -0.0101 10.06 0.869 -0.0023 8.99 0.832 -0.0043 7.84 0.748 -0.0057 6.67 0.653 -0.0091 5.88 0.580 -0.0104 4.64 0.455 -0.0105 3.78 0.368 -0.0102 2.86 0.272 -0.0098 1.48 0.127 -0.0088 0.48 0.024 -0.0084 -0.44 -0.073 -0.0080 -1.39 -0.173 -0.0076 -2.34 -0.274 -0.0073 -3.33 -0.379 -0.0070 -4.40 -0.489 -0.0066 -5.52 -0.600 -0.0070 -6.64 -0.706 -0.0064 Tabulated from data in file CL01685.DAT & reduced using program Q06.01L Average Reynolds #: 507200 Number of angles of attack: 49 alpha / Cl / Cm -6.22 -0.663 -0.0095 -4.55 -0.502 -0.0113 -3.40 -0.387 -0.0112 -2.68 -0.310 -0.0114 -1.41 -0.171 -0.0119 -0.05 -0.025 -0.0123 0.24 0.005 -0.0108 1.50 0.134 -0.0130 2.79 0.270 -0.0143 3.50 0.337 -0.0146 4.67 0.468 -0.0163 5.90 0.601 -0.0169 6.57 0.645 -0.0154 7.74 0.758 -0.0135 8.84 0.834 -0.0108 9.86 0.879 -0.0078 10.78 0.894 -0.0142 11.72 0.891 -0.0231 12.74 0.887 -0.0345 13.88 0.891 -0.0423 14.99 0.885 -0.0473 15.69 0.880 -0.0492 16.77 0.886 -0.0536 17.92 0.907 -0.0590 18.84 0.935 -0.0649 16.58 0.885 -0.0528 15.88 0.886 -0.0497 14.81 0.887 -0.0467 13.78 0.890 -0.0409 12.86 0.908 -0.0341 11.99 0.889 -0.0267 10.87 0.883 -0.0135 9.93 0.858 0.0005 9.04 0.824 0.0009 7.96 0.754 -0.0026 6.76 0.663 -0.0062 5.90 0.604 -0.0081 4.95 0.488 -0.0072 3.54 0.338 -0.0060 2.95 0.278 -0.0060 1.40 0.123 -0.0056 0.78 0.050 -0.0050 -0.35 -0.066 -0.0042 -1.50 -0.195 -0.0027 -2.60 -0.314 -0.0016 -3.26 -0.387 -0.0005 -4.40 -0.503 0.0006 -5.64 -0.623 0.0010 -6.46 -0.700 0.0011 Tabulated from data in file CL01860.DAT & reduced using program Q06.01L File US1000.LFT created on 10-24-1997 at 19:34:42 using program FORMAT :::::::::::::: USNPS4.LFT :::::::::::::: Airfoil: USNPS-4 Builder: J. Raley Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 100800 Number of angles of attack: 49 alpha / Cl / Cm -4.73 -0.330 -0.0027 -3.41 -0.161 -0.0478 -2.03 0.020 -0.0697 -1.30 0.119 -0.0741 0.08 0.329 -0.0833 0.87 0.491 -0.0922 2.24 0.748 -0.1043 2.99 0.814 -0.1013 4.36 0.919 -0.0938 5.15 0.976 -0.0886 5.92 1.023 -0.0829 7.34 1.112 -0.0747 8.08 1.167 -0.0709 9.49 1.283 -0.0653 10.22 1.323 -0.0615 10.93 1.373 -0.0584 12.27 1.429 -0.0500 12.83 0.890 -0.0991 14.18 0.888 -0.1049 14.90 0.892 -0.1064 16.30 0.941 -0.1155 17.08 0.958 -0.1175 17.84 0.947 -0.1158 19.28 1.030 -0.1338 20.02 1.039 -0.1342 18.14 0.946 -0.1297 16.87 0.948 -0.1265 15.64 0.918 -0.1220 14.98 0.904 -0.1204 14.30 0.895 -0.1195 13.10 0.870 -0.1097 11.90 0.911 -0.1070 11.29 0.983 -0.1058 10.19 1.324 -0.0731 9.00 1.243 -0.0744 7.80 1.153 -0.0784 7.12 1.103 -0.0797 5.85 1.020 -0.0873 5.18 0.979 -0.0921 3.90 0.890 -0.1003 3.22 0.838 -0.1044 1.99 0.714 -0.1094 0.72 0.471 -0.0978 0.04 0.321 -0.0877 -1.18 0.136 -0.0810 -2.44 -0.017 -0.0734 -3.15 -0.120 -0.0628 -4.39 -0.304 -0.0200 -5.07 -0.350 -0.0039 Tabulated from data in file PG01165.DAT & reduced using program Q06.01L Average Reynolds #: 200500 Number of angles of attack: 49 alpha / Cl / Cm -4.65 -0.131 -0.0719 -3.16 0.136 -0.1152 -2.34 0.262 -0.1216 -1.19 0.415 -0.1242 -0.37 0.506 -0.1230 0.91 0.642 -0.1207 1.76 0.731 -0.1191 2.99 0.843 -0.1132 3.81 0.904 -0.1069 5.07 0.992 -0.0973 5.88 1.049 -0.0927 7.12 1.142 -0.0860 7.90 1.201 -0.0818 9.08 1.286 -0.0750 9.85 1.337 -0.0707 10.96 1.414 -0.0643 12.06 1.479 -0.0578 13.15 1.533 -0.0502 14.21 1.576 -0.0446 14.89 1.597 -0.0406 16.30 1.636 -0.0349 16.99 1.653 -0.0340 18.05 1.679 -0.0359 19.09 1.652 -0.0559 20.10 1.626 -0.0911 17.92 1.016 -0.1456 17.11 0.954 -0.1358 15.93 0.945 -0.1341 15.20 0.920 -0.1309 14.11 0.893 -0.1278 13.05 0.896 -0.1254 12.32 0.932 -0.1232 11.49 1.448 -0.0627 10.24 1.363 -0.0686 9.30 1.296 -0.0736 8.31 1.226 -0.0792 7.27 1.153 -0.0852 6.21 1.073 -0.0908 5.11 0.991 -0.0971 4.35 0.940 -0.1027 3.23 0.859 -0.1115 2.11 0.761 -0.1176 0.97 0.646 -0.1215 0.19 0.563 -0.1224 -1.00 0.434 -0.1250 -1.92 0.320 -0.1246 -3.13 0.140 -0.1172 -3.87 0.010 -0.1038 -5.03 -0.202 -0.0571 Tabulated from data in file PG01167.DAT & reduced using program Q06.01L Average Reynolds #: 300400 Number of angles of attack: 49 alpha / Cl / Cm -4.64 -0.009 -0.1041 -3.37 0.163 -0.1250 -2.52 0.274 -0.1260 -1.36 0.407 -0.1227 -0.41 0.503 -0.1192 0.86 0.631 -0.1159 1.84 0.738 -0.1154 2.91 0.835 -0.1108 4.01 0.915 -0.1024 4.82 0.972 -0.0965 6.04 1.065 -0.0901 6.94 1.137 -0.0856 7.87 1.206 -0.0808 9.28 1.309 -0.0729 10.15 1.372 -0.0680 10.98 1.429 -0.0632 12.18 1.504 -0.0558 12.96 1.548 -0.0511 14.07 1.604 -0.0442 15.14 1.651 -0.0386 15.92 1.674 -0.0365 16.88 1.656 -0.0544 18.38 1.695 -0.0692 18.81 1.685 -0.0802 19.86 1.646 -0.0903 18.43 1.688 -0.0730 17.37 1.673 -0.0584 16.42 1.676 -0.0416 15.49 1.659 -0.0388 14.20 1.609 -0.0443 13.21 1.559 -0.0502 12.21 1.502 -0.0564 11.15 1.438 -0.0634 10.42 1.390 -0.0669 9.28 1.309 -0.0731 8.04 1.217 -0.0804 7.18 1.153 -0.0854 6.27 1.082 -0.0901 5.22 0.998 -0.0954 3.89 0.904 -0.1051 3.04 0.841 -0.1116 2.22 0.771 -0.1161 1.03 0.650 -0.1185 -0.12 0.532 -0.1206 -0.87 0.458 -0.1226 -2.00 0.339 -0.1267 -2.99 0.213 -0.1285 -4.14 0.073 -0.1188 -5.14 -0.084 -0.0891 Tabulated from data in file PG01510.DAT & reduced using program Q06.01L Average Reynolds #: 401800 Number of angles of attack: 49 alpha / Cl / Cm -6.70 -0.216 -0.0428 -5.43 -0.060 -0.0932 -4.44 0.054 -0.1175 -3.49 0.172 -0.1269 -2.33 0.308 -0.1256 -1.36 0.409 -0.1216 -0.35 0.511 -0.1186 0.76 0.620 -0.1165 1.64 0.719 -0.1163 2.90 0.822 -0.1094 4.00 0.898 -0.1012 4.83 0.965 -0.0964 6.10 1.069 -0.0897 7.03 1.142 -0.0843 7.96 1.214 -0.0792 8.98 1.292 -0.0733 10.13 1.374 -0.0666 11.26 1.448 -0.0599 12.34 1.513 -0.0541 12.96 1.550 -0.0502 14.46 1.630 -0.0444 15.01 1.654 -0.0425 16.44 1.692 -0.0492 17.37 1.697 -0.0636 18.17 1.648 -0.0862 16.17 1.667 -0.0503 15.38 1.664 -0.0404 14.35 1.622 -0.0388 13.20 1.563 -0.0448 12.35 1.515 -0.0487 11.06 1.431 -0.0561 10.15 1.371 -0.0620 9.16 1.301 -0.0676 8.05 1.217 -0.0747 6.77 1.117 -0.0815 6.16 1.067 -0.0822 4.97 0.971 -0.0888 3.91 0.888 -0.0949 2.91 0.820 -0.1036 2.01 0.747 -0.1096 1.14 0.657 -0.1126 -0.10 0.533 -0.1158 -0.92 0.451 -0.1192 -2.06 0.337 -0.1239 -3.17 0.216 -0.1283 -4.06 0.105 -0.1240 -5.11 -0.012 -0.1071 -5.95 -0.131 -0.0741 -6.97 -0.244 -0.0349 Tabulated from data in file PG01512.DAT & reduced using program Q06.01L File USNPS4.LFT created on 10-24-1997 at 19:34:42 using program FORMAT