Airfoil: S7075 (A) Builder: J. Robertson Comment: plain trip @ x/c = 68% (h/c = 0.17%; w/c = 2.0%) Number of Reynolds #'s: 3 Average Reynolds #: 100800 Number of angles of attack: 49 alpha / Cl / Cm -6.13 -0.411 -0.0800 -4.81 -0.242 -0.0800 -3.82 -0.155 -0.0800 -2.79 -0.052 -0.0800 -1.85 0.040 -0.0800 -0.67 0.138 -0.0800 0.23 0.246 -0.0800 1.31 0.382 -0.0800 2.41 0.553 -0.0800 3.35 0.674 -0.0800 4.46 0.783 -0.0800 5.54 0.873 -0.0800 6.52 0.949 -0.0800 7.44 1.023 -0.0800 8.49 1.092 -0.0800 9.51 1.130 -0.0800 10.63 1.176 -0.0800 11.53 1.203 -0.0800 12.61 1.214 -0.0800 13.56 1.085 -0.0800 14.53 1.021 -0.0800 15.51 1.014 -0.0800 16.58 1.018 -0.0800 17.46 1.014 -0.0800 18.54 0.952 -0.0800 17.17 1.005 -0.0800 16.02 1.000 -0.0800 15.18 1.018 -0.0800 14.16 1.067 -0.0800 13.21 1.177 -0.0800 12.31 1.218 -0.0800 11.16 1.192 -0.0800 10.11 1.152 -0.0800 9.19 1.115 -0.0800 8.04 1.065 -0.0800 7.18 0.999 -0.0800 6.19 0.920 -0.0800 4.99 0.820 -0.0800 3.95 0.728 -0.0800 3.11 0.640 -0.0800 2.02 0.491 -0.0800 0.97 0.330 -0.0800 0.01 0.206 -0.0800 -1.11 0.084 -0.0800 -2.03 0.020 -0.0800 -3.15 -0.096 -0.0800 -4.11 -0.178 -0.0800 -5.13 -0.277 -0.0800 -6.14 -0.403 -0.0800 Tabulated from data in file CL00699.DAT & reduced using program Q02.00L Average Reynolds #: 200800 Number of angles of attack: 49 alpha / Cl / Cm -6.15 -0.283 -0.0800 -4.73 -0.116 -0.0800 -3.62 -0.014 -0.0800 -2.70 0.077 -0.0800 -1.58 0.186 -0.0800 -0.67 0.271 -0.0800 0.35 0.355 -0.0800 1.36 0.469 -0.0800 2.35 0.570 -0.0800 3.45 0.689 -0.0800 4.45 0.790 -0.0800 5.55 0.884 -0.0800 6.46 0.956 -0.0800 7.54 1.037 -0.0800 8.61 1.102 -0.0800 9.65 1.151 -0.0800 10.64 1.189 -0.0800 11.54 1.216 -0.0800 12.65 1.225 -0.0800 13.46 1.138 -0.0800 14.51 1.047 -0.0800 15.53 1.010 -0.0800 16.45 1.002 -0.0800 17.58 0.966 -0.0800 18.49 0.951 -0.0800 17.04 0.996 -0.0800 16.14 1.012 -0.0800 15.13 1.040 -0.0800 14.11 1.123 -0.0800 13.34 1.211 -0.0800 12.13 1.222 -0.0800 11.11 1.201 -0.0800 10.15 1.166 -0.0800 9.09 1.117 -0.0800 8.12 1.070 -0.0800 7.09 0.998 -0.0800 5.98 0.909 -0.0800 5.09 0.834 -0.0800 4.13 0.752 -0.0800 2.94 0.617 -0.0800 2.02 0.527 -0.0800 0.81 0.400 -0.0800 -0.12 0.300 -0.0800 -1.25 0.214 -0.0800 -2.23 0.121 -0.0800 -3.21 0.022 -0.0800 -4.19 -0.072 -0.0800 -5.27 -0.173 -0.0800 -6.30 -0.304 -0.0800 Tabulated from data in file CL00701.DAT & reduced using program Q02.00L Average Reynolds #: 300900 Number of angles of attack: 49 alpha / Cl / Cm -6.13 -0.265 -0.0800 -4.79 -0.122 -0.0800 -3.75 -0.028 -0.0800 -2.63 0.078 -0.0800 -1.56 0.166 -0.0800 -0.66 0.257 -0.0800 0.45 0.396 -0.0800 1.43 0.498 -0.0800 2.43 0.605 -0.0800 3.48 0.709 -0.0800 4.50 0.803 -0.0800 5.49 0.890 -0.0800 6.46 0.972 -0.0800 7.62 1.062 -0.0800 8.55 1.123 -0.0800 9.61 1.183 -0.0800 10.60 1.223 -0.0800 11.55 1.249 -0.0800 12.54 1.258 -0.0800 13.56 1.249 -0.0800 14.43 1.130 -0.0800 15.40 1.070 -0.0800 16.36 1.050 -0.0800 17.34 1.009 -0.0800 18.42 0.966 -0.0800 17.05 1.010 -0.0800 15.97 1.045 -0.0800 14.97 1.092 -0.0800 14.26 1.171 -0.0800 13.24 1.249 -0.0800 12.25 1.257 -0.0800 11.21 1.238 -0.0800 10.07 1.198 -0.0800 9.15 1.151 -0.0800 8.18 1.094 -0.0800 7.02 1.007 -0.0800 5.99 0.924 -0.0800 5.11 0.848 -0.0800 3.92 0.739 -0.0800 3.02 0.656 -0.0800 1.99 0.548 -0.0800 0.88 0.433 -0.0800 -0.13 0.323 -0.0800 -1.16 0.203 -0.0800 -2.32 0.103 -0.0800 -3.33 0.004 -0.0800 -4.32 -0.086 -0.0800 -5.36 -0.183 -0.0800 -6.23 -0.278 -0.0800 Tabulated from data in file CL00704.DAT & reduced using program Q02.00L File 7075at1.lft created on 09-12-1997 at 13:46:18 using program FORMAT