Airfoil: SD7037 (C) Builder: D. Brengman Comment: gurney flap (h/c = 0.4%) Number of Reynolds #'s: 4 Average Reynolds #: 60300 Number of angles of attack: 51 alpha / Cl / Cm -5.57 -0.249 -0.0850 -3.90 -0.137 -0.0850 -2.97 -0.062 -0.0850 -2.08 0.004 -0.0850 -0.93 0.117 -0.0850 -0.06 0.205 -0.0850 1.14 0.376 -0.0850 2.02 0.492 -0.0850 3.20 0.634 -0.0850 4.08 0.721 -0.0850 5.30 0.829 -0.0850 6.21 0.903 -0.0850 7.15 0.978 -0.0850 8.38 1.065 -0.0850 9.27 1.128 -0.0850 10.20 1.184 -0.0850 11.38 1.224 -0.0850 12.22 1.234 -0.0850 13.25 1.068 -0.0850 14.37 1.075 -0.0850 15.36 1.034 -0.0850 16.26 1.037 -0.0850 17.22 1.026 -0.0850 18.33 1.051 -0.0850 19.23 1.032 -0.0850 20.42 1.061 -0.0850 18.75 1.107 -0.0850 17.85 1.097 -0.0850 16.76 1.093 -0.0850 15.66 1.106 -0.0850 14.67 1.098 -0.0850 13.82 1.050 -0.0850 12.85 1.081 -0.0850 11.70 1.073 -0.0850 10.81 1.239 -0.0850 9.89 1.206 -0.0850 8.70 1.130 -0.0850 7.83 1.068 -0.0850 6.81 0.986 -0.0850 5.60 0.899 -0.0850 4.79 0.836 -0.0850 3.55 0.722 -0.0850 2.72 0.634 -0.0850 1.68 0.511 -0.0850 0.49 0.345 -0.0850 -0.33 0.242 -0.0850 -1.50 0.131 -0.0850 -2.50 0.054 -0.0850 -3.47 -0.020 -0.0850 -4.65 -0.118 -0.0850 -5.64 -0.184 -0.0850 Tabulated from data in file CN00900.DAT & reduced using program Q02.00L Average Reynolds #: 100300 Number of angles of attack: 51 alpha / Cl / Cm -5.57 -0.248 -0.0850 -4.08 -0.105 -0.0850 -2.87 0.023 -0.0850 -1.96 0.108 -0.0850 -1.02 0.187 -0.0850 0.21 0.380 -0.0850 1.02 0.485 -0.0850 2.26 0.614 -0.0850 3.16 0.703 -0.0850 4.33 0.818 -0.0850 5.24 0.907 -0.0850 6.16 0.991 -0.0850 7.28 1.091 -0.0850 8.43 1.166 -0.0850 9.34 1.227 -0.0850 10.28 1.285 -0.0850 11.56 1.320 -0.0850 12.33 1.326 -0.0850 13.18 1.313 -0.0850 14.67 1.157 -0.0850 15.39 1.123 -0.0850 16.32 1.075 -0.0850 17.43 1.087 -0.0850 18.38 1.054 -0.0850 19.60 1.072 -0.0850 20.24 1.075 -0.0850 18.98 1.047 -0.0850 18.04 1.081 -0.0850 17.12 1.103 -0.0850 15.71 1.107 -0.0850 14.67 1.162 -0.0850 13.75 1.148 -0.0850 12.98 1.103 -0.0850 11.94 1.320 -0.0850 10.75 1.310 -0.0850 9.74 1.264 -0.0850 8.83 1.195 -0.0850 7.69 1.128 -0.0850 6.79 1.055 -0.0850 5.73 0.962 -0.0850 4.73 0.867 -0.0850 3.70 0.769 -0.0850 2.74 0.674 -0.0850 1.50 0.554 -0.0850 0.66 0.459 -0.0850 -0.59 0.278 -0.0850 -1.40 0.156 -0.0850 -3.04 0.074 -0.0850 -3.44 0.016 -0.0850 -4.80 -0.115 -0.0850 -6.05 -0.219 -0.0850 Tabulated from data in file CN00902.DAT & reduced using program Q02.00L Average Reynolds #: 200400 Number of angles of attack: 51 alpha / Cl / Cm -5.56 -0.198 -0.0850 -3.80 -0.014 -0.0850 -3.03 0.079 -0.0850 -1.91 0.240 -0.0850 -0.95 0.328 -0.0850 0.32 0.416 -0.0850 1.05 0.492 -0.0850 2.11 0.606 -0.0850 3.18 0.722 -0.0850 4.25 0.833 -0.0850 5.30 0.937 -0.0850 6.35 1.036 -0.0850 7.40 1.127 -0.0850 8.40 1.203 -0.0850 9.42 1.274 -0.0850 10.39 1.326 -0.0850 11.34 1.349 -0.0850 12.27 1.334 -0.0850 13.46 1.309 -0.0850 14.23 1.285 -0.0850 15.20 1.220 -0.0850 16.33 1.170 -0.0850 17.36 1.079 -0.0850 18.26 1.075 -0.0850 19.38 1.070 -0.0850 20.40 1.074 -0.0850 18.66 1.076 -0.0850 17.69 1.083 -0.0850 16.61 1.142 -0.0850 15.56 1.195 -0.0850 14.65 1.214 -0.0850 13.78 1.210 -0.0850 12.74 1.325 -0.0850 11.83 1.346 -0.0850 10.80 1.341 -0.0850 9.74 1.291 -0.0850 8.88 1.235 -0.0850 7.66 1.143 -0.0850 6.73 1.064 -0.0850 5.66 0.965 -0.0850 4.74 0.873 -0.0850 3.69 0.766 -0.0850 2.51 0.641 -0.0850 1.56 0.541 -0.0850 0.37 0.416 -0.0850 -0.62 0.325 -0.0850 -1.60 0.275 -0.0850 -2.63 0.129 -0.0850 -3.65 -0.006 -0.0850 -4.56 -0.104 -0.0850 -5.72 -0.221 -0.0850 Tabulated from data in file CN00904.DAT & reduced using program Q02.00L Average Reynolds #: 300500 Number of angles of attack: 51 alpha / Cl / Cm -5.67 -0.194 -0.0850 -3.83 0.023 -0.0850 -2.97 0.132 -0.0850 -1.80 0.266 -0.0850 -0.92 0.348 -0.0850 0.24 0.408 -0.0850 1.30 0.528 -0.0850 2.36 0.647 -0.0850 3.12 0.729 -0.0850 4.48 0.874 -0.0850 5.28 0.952 -0.0850 6.32 1.052 -0.0850 7.35 1.142 -0.0850 8.39 1.229 -0.0850 9.36 1.303 -0.0850 10.34 1.359 -0.0850 11.29 1.378 -0.0850 12.46 1.361 -0.0850 13.26 1.336 -0.0850 14.45 1.285 -0.0850 15.29 1.258 -0.0850 15.99 1.269 -0.0850 17.11 1.168 -0.0850 18.18 1.095 -0.0850 19.10 1.077 -0.0850 20.09 1.072 -0.0850 18.65 1.081 -0.0850 17.69 1.102 -0.0850 16.69 1.221 -0.0850 15.80 1.260 -0.0850 14.93 1.304 -0.0850 13.65 1.317 -0.0850 12.76 1.352 -0.0850 11.67 1.372 -0.0850 10.86 1.370 -0.0850 9.76 1.323 -0.0850 8.73 1.252 -0.0850 7.53 1.156 -0.0850 6.48 1.063 -0.0850 5.54 0.977 -0.0850 4.52 0.875 -0.0850 3.47 0.764 -0.0850 2.54 0.663 -0.0850 1.44 0.541 -0.0850 0.65 0.454 -0.0850 -0.46 0.364 -0.0850 -1.51 0.295 -0.0850 -2.53 0.187 -0.0850 -3.47 0.070 -0.0850 -4.54 -0.064 -0.0850 -5.81 -0.205 -0.0850 Tabulated from data in file AG00906.DAT & reduced using program Q02.00L File 7037cbf4.lft created on 09-12-1997 at 13:46:19 using program FORMAT