Airfoil: S7075 (A) Builder: J. Robertson Comment: Zig-Zag trip type "D" @ x/c = 68% (h/c = 0.39%) Number of Reynolds #'s: 3 Average Reynolds #: 100400 Number of angles of attack: 49 alpha / Cl / Cm -6.15 -0.285 -0.0800 -4.56 -0.119 -0.0800 -3.62 -0.035 -0.0800 -2.73 0.048 -0.0800 -1.64 0.136 -0.0800 -0.77 0.235 -0.0800 0.27 0.306 -0.0800 1.56 0.432 -0.0800 2.45 0.568 -0.0800 3.55 0.702 -0.0800 4.52 0.794 -0.0800 5.50 0.877 -0.0800 6.68 0.962 -0.0800 7.44 1.027 -0.0800 8.61 1.097 -0.0800 9.73 1.143 -0.0800 10.66 1.182 -0.0800 11.54 1.204 -0.0800 12.52 1.214 -0.0800 13.51 1.041 -0.0800 14.50 1.026 -0.0800 15.70 1.003 -0.0800 16.64 1.019 -0.0800 17.47 0.989 -0.0800 18.59 0.964 -0.0800 17.15 1.003 -0.0800 16.01 1.028 -0.0800 15.11 1.011 -0.0800 14.01 1.053 -0.0800 13.07 1.144 -0.0800 12.07 1.218 -0.0800 11.06 1.191 -0.0800 10.03 1.149 -0.0800 9.09 1.110 -0.0800 8.10 1.072 -0.0800 7.03 0.982 -0.0800 5.94 0.897 -0.0800 5.03 0.831 -0.0800 4.08 0.743 -0.0800 2.95 0.622 -0.0800 2.06 0.498 -0.0800 0.95 0.356 -0.0800 -0.18 0.292 -0.0800 -1.20 0.176 -0.0800 -2.18 0.087 -0.0800 -3.08 0.011 -0.0800 -4.20 -0.089 -0.0800 -5.17 -0.175 -0.0800 -6.16 -0.279 -0.0800 Tabulated from data in file CL00716.DAT & reduced using program Q02.00L Average Reynolds #: 200700 Number of angles of attack: 49 alpha / Cl / Cm -6.12 -0.281 -0.0800 -4.65 -0.121 -0.0800 -3.61 -0.025 -0.0800 -2.53 0.075 -0.0800 -1.54 0.168 -0.0800 -0.50 0.266 -0.0800 0.40 0.358 -0.0800 1.40 0.467 -0.0800 2.40 0.579 -0.0800 3.67 0.713 -0.0800 4.47 0.790 -0.0800 5.73 0.896 -0.0800 6.49 0.957 -0.0800 7.51 1.038 -0.0800 8.52 1.102 -0.0800 9.76 1.160 -0.0800 10.70 1.194 -0.0800 11.61 1.221 -0.0800 12.53 1.232 -0.0800 13.39 1.178 -0.0800 14.60 1.071 -0.0800 15.54 1.040 -0.0800 16.59 1.019 -0.0800 17.58 0.983 -0.0800 18.70 0.965 -0.0800 16.94 1.026 -0.0800 16.02 1.007 -0.0800 15.13 1.052 -0.0800 13.98 1.144 -0.0800 13.22 1.228 -0.0800 12.20 1.229 -0.0800 11.18 1.205 -0.0800 9.96 1.162 -0.0800 9.13 1.123 -0.0800 7.93 1.057 -0.0800 6.94 0.982 -0.0800 5.89 0.896 -0.0800 5.11 0.831 -0.0800 4.01 0.732 -0.0800 2.96 0.625 -0.0800 1.93 0.512 -0.0800 0.80 0.391 -0.0800 -0.06 0.301 -0.0800 -1.31 0.180 -0.0800 -2.18 0.104 -0.0800 -3.13 0.015 -0.0800 -4.33 -0.094 -0.0800 -5.32 -0.182 -0.0800 -6.31 -0.297 -0.0800 Tabulated from data in file CL00718.DAT & reduced using program Q02.00L Average Reynolds #: 301100 Number of angles of attack: 49 alpha / Cl / Cm -5.88 -0.234 -0.0800 -4.36 -0.086 -0.0800 -3.32 0.009 -0.0800 -2.62 0.076 -0.0800 -1.38 0.184 -0.0800 -0.60 0.254 -0.0800 0.58 0.383 -0.0800 1.68 0.504 -0.0800 2.77 0.624 -0.0800 3.56 0.704 -0.0800 4.44 0.780 -0.0800 5.62 0.886 -0.0800 6.53 0.962 -0.0800 7.52 1.040 -0.0800 8.62 1.111 -0.0800 9.55 1.163 -0.0800 10.56 1.200 -0.0800 11.70 1.229 -0.0800 12.75 1.241 -0.0800 13.62 1.236 -0.0800 14.61 1.145 -0.0800 15.44 1.074 -0.0800 16.50 1.035 -0.0800 17.49 1.008 -0.0800 18.53 0.946 -0.0800 16.83 1.028 -0.0800 16.06 1.047 -0.0800 15.17 1.085 -0.0800 13.98 1.213 -0.0800 13.45 1.236 -0.0800 12.12 1.235 -0.0800 10.95 1.208 -0.0800 10.00 1.177 -0.0800 9.04 1.128 -0.0800 7.95 1.061 -0.0800 6.89 0.979 -0.0800 5.77 0.888 -0.0800 4.91 0.811 -0.0800 3.93 0.723 -0.0800 2.99 0.632 -0.0800 1.78 0.502 -0.0800 0.78 0.394 -0.0800 -0.13 0.289 -0.0800 -1.39 0.170 -0.0800 -2.49 0.075 -0.0800 -3.45 -0.016 -0.0800 -4.36 -0.098 -0.0800 -5.29 -0.182 -0.0800 -6.45 -0.312 -0.0800 Tabulated from data in file CL00720.DAT & reduced using program Q02.00L File 7075at3.lft created on 09-12-1997 at 13:46:18 using program FORMAT