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