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