Airfoil: SD7037 (B) Builder: D. Thompson Comment: clean: flap = 5 degs Number of Reynolds #'s: 4 Average Reynolds #: 60600 Number of angles of attack: 49 alpha / Cl / Cm -5.96 -0.188 -0.1000 -4.54 -0.043 -0.1000 -3.44 0.056 -0.1000 -2.61 0.123 -0.1000 -1.50 0.219 -0.1000 -0.39 0.327 -0.1000 0.69 0.445 -0.1000 1.52 0.563 -0.1000 2.65 0.750 -0.1000 3.58 0.882 -0.1000 4.78 0.981 -0.1000 5.72 1.050 -0.1000 6.70 1.114 -0.1000 7.93 1.167 -0.1000 8.88 1.217 -0.1000 9.81 1.261 -0.1000 10.71 1.294 -0.1000 11.83 1.315 -0.1000 12.82 1.033 -0.1000 13.68 1.041 -0.1000 14.83 1.073 -0.1000 15.73 1.032 -0.1000 16.67 1.044 -0.1000 17.71 1.078 -0.1000 18.87 1.066 -0.1000 17.21 1.060 -0.1000 16.28 1.077 -0.1000 15.34 1.073 -0.1000 14.23 1.062 -0.1000 13.24 1.002 -0.1000 12.36 1.051 -0.1000 11.30 1.089 -0.1000 10.30 1.280 -0.1000 9.40 1.243 -0.1000 8.26 1.189 -0.1000 7.31 1.147 -0.1000 6.34 1.094 -0.1000 5.20 1.013 -0.1000 4.23 0.941 -0.1000 3.28 0.850 -0.1000 2.16 0.669 -0.1000 1.06 0.509 -0.1000 0.14 0.390 -0.1000 -0.89 0.294 -0.1000 -1.96 0.188 -0.1000 -2.89 0.116 -0.1000 -3.92 0.025 -0.1000 -4.98 -0.074 -0.1000 -6.00 -0.187 -0.1000 Tabulated from data in file CL00805.DAT & reduced using program Q02.00L Average Reynolds #: 100000 Number of angles of attack: 49 alpha / Cl / Cm -5.97 -0.099 -0.1000 -4.37 0.023 -0.1000 -3.47 0.118 -0.1000 -2.31 0.224 -0.1000 -1.42 0.278 -0.1000 -0.27 0.407 -0.1000 0.52 0.522 -0.1000 1.61 0.696 -0.1000 2.72 0.831 -0.1000 3.66 0.908 -0.1000 4.87 1.004 -0.1000 5.80 1.080 -0.1000 6.91 1.169 -0.1000 7.86 1.218 -0.1000 8.81 1.258 -0.1000 9.73 1.296 -0.1000 10.73 1.327 -0.1000 11.83 1.341 -0.1000 12.79 1.333 -0.1000 13.78 1.081 -0.1000 14.83 1.065 -0.1000 15.79 1.110 -0.1000 16.74 1.085 -0.1000 17.72 1.050 -0.1000 18.87 1.061 -0.1000 17.16 1.104 -0.1000 16.26 1.112 -0.1000 15.27 1.099 -0.1000 14.26 1.077 -0.1000 13.29 1.089 -0.1000 12.34 1.334 -0.1000 11.38 1.329 -0.1000 10.26 1.310 -0.1000 9.29 1.270 -0.1000 8.36 1.228 -0.1000 7.38 1.183 -0.1000 6.16 1.091 -0.1000 5.37 1.029 -0.1000 4.22 0.937 -0.1000 3.25 0.861 -0.1000 2.27 0.763 -0.1000 1.10 0.612 -0.1000 0.12 0.445 -0.1000 -0.95 0.315 -0.1000 -2.02 0.233 -0.1000 -3.00 0.157 -0.1000 -3.91 0.069 -0.1000 -5.04 -0.032 -0.1000 -5.97 -0.097 -0.1000 Tabulated from data in file CL00807.DAT & reduced using program Q02.00L Average Reynolds #: 200200 Number of angles of attack: 49 alpha / Cl / Cm -5.95 -0.013 -0.1000 -4.25 0.149 -0.1000 -3.29 0.238 -0.1000 -2.22 0.336 -0.1000 -1.36 0.423 -0.1000 -0.44 0.512 -0.1000 0.49 0.601 -0.1000 1.60 0.729 -0.1000 2.70 0.829 -0.1000 3.75 0.924 -0.1000 4.69 1.007 -0.1000 5.69 1.090 -0.1000 6.71 1.164 -0.1000 7.73 1.224 -0.1000 8.61 1.270 -0.1000 9.75 1.323 -0.1000 10.90 1.360 -0.1000 11.85 1.370 -0.1000 12.91 1.354 -0.1000 13.70 1.326 -0.1000 14.58 1.115 -0.1000 15.96 1.113 -0.1000 16.67 1.108 -0.1000 17.71 1.115 -0.1000 18.89 1.058 -0.1000 17.11 1.129 -0.1000 16.23 1.123 -0.1000 14.98 1.081 -0.1000 14.12 1.092 -0.1000 13.28 1.336 -0.1000 12.30 1.367 -0.1000 11.34 1.365 -0.1000 10.35 1.339 -0.1000 9.30 1.296 -0.1000 8.35 1.249 -0.1000 7.23 1.187 -0.1000 6.09 1.112 -0.1000 5.16 1.036 -0.1000 4.26 0.958 -0.1000 3.16 0.858 -0.1000 2.03 0.760 -0.1000 1.21 0.663 -0.1000 -0.02 0.535 -0.1000 -0.90 0.464 -0.1000 -2.00 0.356 -0.1000 -3.02 0.258 -0.1000 -4.07 0.161 -0.1000 -5.03 0.069 -0.1000 -6.15 -0.034 -0.1000 Tabulated from data in file CL00809.DAT & reduced using program Q02.00L Average Reynolds #: 300100 Number of angles of attack: 49 alpha / Cl / Cm -5.91 -0.014 -0.1000 -4.45 0.125 -0.1000 -3.50 0.215 -0.1000 -2.66 0.324 -0.1000 -1.41 0.455 -0.1000 -0.53 0.539 -0.1000 0.49 0.633 -0.1000 1.62 0.742 -0.1000 2.77 0.848 -0.1000 3.72 0.935 -0.1000 4.62 1.015 -0.1000 5.81 1.115 -0.1000 6.73 1.181 -0.1000 7.79 1.248 -0.1000 8.90 1.312 -0.1000 9.72 1.354 -0.1000 10.80 1.396 -0.1000 11.80 1.407 -0.1000 12.83 1.384 -0.1000 13.68 1.352 -0.1000 14.94 1.307 -0.1000 15.47 1.158 -0.1000 16.60 1.173 -0.1000 17.58 1.142 -0.1000 18.52 1.122 -0.1000 17.35 1.131 -0.1000 16.36 1.184 -0.1000 15.30 1.168 -0.1000 14.73 1.314 -0.1000 13.27 1.367 -0.1000 12.36 1.394 -0.1000 11.26 1.401 -0.1000 10.34 1.378 -0.1000 9.25 1.326 -0.1000 8.17 1.264 -0.1000 7.25 1.207 -0.1000 6.08 1.129 -0.1000 5.13 1.052 -0.1000 4.25 0.975 -0.1000 3.15 0.874 -0.1000 2.10 0.774 -0.1000 1.06 0.677 -0.1000 0.07 0.582 -0.1000 -0.87 0.490 -0.1000 -1.96 0.379 -0.1000 -3.11 0.238 -0.1000 -3.88 0.159 -0.1000 -5.11 0.047 -0.1000 -6.05 -0.041 -0.1000 Tabulated from data in file CL00811.DAT & reduced using program Q02.00L File 7037bf5.lft created on 09-12-1997 at 13:46:18 using program FORMAT