Airfoil: SD7037 (C) Builder: D. Brengman Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60300 Number of angles of attack: 49 alpha / Cl / Cm -6.39 -0.370 -0.0850 -5.27 -0.285 -0.0850 -4.20 -0.208 -0.0850 -3.12 -0.121 -0.0850 -2.21 -0.048 -0.0850 -1.20 0.052 -0.0850 -0.07 0.173 -0.0850 0.93 0.318 -0.0850 1.94 0.449 -0.0850 2.98 0.591 -0.0850 4.03 0.704 -0.0850 5.10 0.804 -0.0850 6.02 0.881 -0.0850 7.14 0.975 -0.0850 8.07 1.042 -0.0850 9.13 1.097 -0.0850 10.20 1.165 -0.0850 11.12 1.210 -0.0850 12.13 1.240 -0.0850 13.09 1.243 -0.0850 14.16 0.999 -0.0850 15.06 1.034 -0.0850 16.07 1.001 -0.0850 17.12 1.041 -0.0850 18.11 0.987 -0.0850 16.88 1.014 -0.0850 15.91 1.033 -0.0850 14.87 1.018 -0.0850 13.88 0.991 -0.0850 12.89 1.027 -0.0850 11.96 1.214 -0.0850 11.00 1.184 -0.0850 9.93 1.123 -0.0850 8.90 1.059 -0.0850 7.90 1.003 -0.0850 6.88 0.925 -0.0850 5.91 0.841 -0.0850 4.77 0.743 -0.0850 3.73 0.640 -0.0850 2.83 0.533 -0.0850 1.74 0.392 -0.0850 0.70 0.250 -0.0850 -0.35 0.104 -0.0850 -1.34 0.009 -0.0850 -2.42 -0.087 -0.0850 -3.38 -0.162 -0.0850 -4.42 -0.239 -0.0850 -5.49 -0.316 -0.0850 -6.43 -0.389 -0.0850 Tabulated from data in file CL00623.DAT & reduced using program Q02.00L Average Reynolds #: 100700 Number of angles of attack: 49 alpha / Cl / Cm -6.47 -0.403 -0.0850 -5.25 -0.287 -0.0850 -4.27 -0.212 -0.0850 -3.25 -0.123 -0.0850 -2.23 -0.023 -0.0850 -1.17 0.093 -0.0850 -0.10 0.270 -0.0850 0.96 0.418 -0.0850 2.01 0.533 -0.0850 3.08 0.637 -0.0850 4.01 0.721 -0.0850 5.18 0.829 -0.0850 6.14 0.910 -0.0850 7.14 0.992 -0.0850 8.11 1.073 -0.0850 9.09 1.127 -0.0850 10.19 1.194 -0.0850 11.27 1.243 -0.0850 12.14 1.251 -0.0850 13.17 1.246 -0.0850 14.09 1.051 -0.0850 15.16 1.059 -0.0850 16.09 0.999 -0.0850 17.04 0.981 -0.0850 18.18 1.009 -0.0850 16.89 0.985 -0.0850 15.92 1.022 -0.0850 14.84 1.060 -0.0850 13.92 1.026 -0.0850 12.95 1.237 -0.0850 12.02 1.239 -0.0850 10.98 1.215 -0.0850 9.94 1.160 -0.0850 8.94 1.101 -0.0850 7.92 1.041 -0.0850 6.84 0.951 -0.0850 5.87 0.867 -0.0850 4.87 0.778 -0.0850 3.75 0.675 -0.0850 2.79 0.589 -0.0850 1.76 0.485 -0.0850 0.76 0.373 -0.0850 -0.25 0.232 -0.0850 -1.39 0.055 -0.0850 -2.38 -0.049 -0.0850 -3.40 -0.146 -0.0850 -4.36 -0.226 -0.0850 -5.44 -0.307 -0.0850 -6.54 -0.410 -0.0850 Tabulated from data in file CL00625.DAT & reduced using program Q02.00L Average Reynolds #: 201000 Number of angles of attack: 49 alpha / Cl / Cm -6.48 -0.417 -0.0850 -5.18 -0.260 -0.0850 -4.26 -0.160 -0.0850 -3.11 -0.019 -0.0850 -2.17 0.110 -0.0850 -0.97 0.230 -0.0850 -0.00 0.326 -0.0850 0.96 0.418 -0.0850 2.10 0.534 -0.0850 3.02 0.628 -0.0850 3.99 0.725 -0.0850 5.09 0.831 -0.0850 6.05 0.921 -0.0850 7.15 1.016 -0.0850 8.15 1.092 -0.0850 9.08 1.156 -0.0850 10.16 1.223 -0.0850 11.18 1.268 -0.0850 12.12 1.277 -0.0850 13.12 1.259 -0.0850 14.11 1.242 -0.0850 15.15 1.210 -0.0850 15.91 1.121 -0.0850 17.25 1.082 -0.0850 18.24 1.017 -0.0850 16.91 1.108 -0.0850 15.87 1.125 -0.0850 14.84 1.134 -0.0850 14.00 1.248 -0.0850 12.99 1.262 -0.0850 12.03 1.278 -0.0850 11.03 1.260 -0.0850 9.99 1.209 -0.0850 8.94 1.139 -0.0850 7.93 1.069 -0.0850 6.85 0.982 -0.0850 5.89 0.899 -0.0850 4.81 0.800 -0.0850 3.80 0.699 -0.0850 2.74 0.593 -0.0850 1.68 0.484 -0.0850 0.70 0.387 -0.0850 -0.30 0.290 -0.0850 -1.32 0.193 -0.0850 -2.48 0.060 -0.0850 -3.37 -0.061 -0.0850 -4.55 -0.197 -0.0850 -5.51 -0.303 -0.0850 -6.50 -0.416 -0.0850 Tabulated from data in file CL00627.DAT & reduced using program Q02.00L Average Reynolds #: 301100 Number of angles of attack: 49 alpha / Cl / Cm -6.49 -0.393 -0.0850 -5.24 -0.217 -0.0850 -4.16 -0.091 -0.0850 -3.14 0.015 -0.0850 -2.00 0.120 -0.0850 -0.98 0.211 -0.0850 0.01 0.307 -0.0850 1.10 0.425 -0.0850 1.99 0.517 -0.0850 3.01 0.623 -0.0850 4.08 0.731 -0.0850 5.16 0.834 -0.0850 6.04 0.914 -0.0850 7.12 1.006 -0.0850 8.17 1.090 -0.0850 9.14 1.163 -0.0850 10.24 1.235 -0.0850 11.27 1.277 -0.0850 12.23 1.279 -0.0850 13.16 1.261 -0.0850 14.25 1.232 -0.0850 15.20 1.194 -0.0850 15.92 1.224 -0.0850 17.12 1.153 -0.0850 18.14 1.158 -0.0850 16.82 1.165 -0.0850 15.79 1.206 -0.0850 15.22 1.190 -0.0850 13.90 1.243 -0.0850 12.93 1.264 -0.0850 11.98 1.280 -0.0850 10.93 1.262 -0.0850 9.91 1.211 -0.0850 8.86 1.138 -0.0850 7.81 1.057 -0.0850 6.83 0.976 -0.0850 5.70 0.877 -0.0850 4.79 0.791 -0.0850 3.68 0.682 -0.0850 2.72 0.584 -0.0850 1.71 0.480 -0.0850 0.61 0.366 -0.0850 -0.51 0.247 -0.0850 -1.47 0.162 -0.0850 -2.45 0.076 -0.0850 -3.61 -0.037 -0.0850 -4.52 -0.139 -0.0850 -5.51 -0.255 -0.0850 -6.52 -0.400 -0.0850 Tabulated from data in file CL00629.DAT & reduced using program Q02.00L File 7037c.lft created on 09-12-1997 at 13:46:19 using program FORMAT