Airfoil: S7075 (A) Builder: J. Robertson Comment: flap = 10 degs: Zig-Zag trip type "D" @ x/c = 68% (h/c = 0.25%) Number of Reynolds #'s: 4 Average Reynolds #: 60500 Number of angles of attack: 49 alpha / Cl / Cm -6.14 -0.041 -0.1200 -4.67 0.140 -0.1200 -3.64 0.231 -0.1200 -2.63 0.299 -0.1200 -1.64 0.390 -0.1200 -0.66 0.477 -0.1200 0.48 0.572 -0.1200 1.50 0.649 -0.1200 2.52 0.707 -0.1200 3.59 1.019 -0.1200 4.47 1.151 -0.1200 5.45 1.232 -0.1200 6.67 1.238 -0.1200 7.53 1.265 -0.1200 8.51 1.296 -0.1200 9.70 1.343 -0.1200 10.58 1.363 -0.1200 11.65 1.333 -0.1200 12.46 1.173 -0.1200 13.58 1.123 -0.1200 14.50 1.145 -0.1200 15.60 1.127 -0.1200 16.55 1.094 -0.1200 17.45 1.116 -0.1200 18.56 1.147 -0.1200 17.02 1.091 -0.1200 16.18 1.102 -0.1200 15.08 1.107 -0.1200 14.01 1.152 -0.1200 13.17 1.139 -0.1200 12.04 1.176 -0.1200 11.08 1.378 -0.1200 10.10 1.362 -0.1200 9.01 1.323 -0.1200 8.15 1.290 -0.1200 7.04 1.254 -0.1200 6.15 1.243 -0.1200 5.21 1.229 -0.1200 4.06 1.142 -0.1200 3.08 0.814 -0.1200 1.94 0.663 -0.1200 0.84 0.604 -0.1200 0.03 0.542 -0.1200 -1.12 0.438 -0.1200 -2.21 0.339 -0.1200 -3.05 0.271 -0.1200 -4.09 0.201 -0.1200 -5.08 0.097 -0.1200 -6.05 -0.025 -0.1200 Tabulated from data in file CL00743.DAT & reduced using program Q02.00L Average Reynolds #: 100300 Number of angles of attack: 49 alpha / Cl / Cm -6.25 -0.040 -0.1200 -4.59 0.145 -0.1200 -3.70 0.227 -0.1200 -2.67 0.322 -0.1200 -1.66 0.396 -0.1200 -0.72 0.498 -0.1200 0.48 0.601 -0.1200 1.34 0.650 -0.1200 2.56 0.868 -0.1200 3.53 1.100 -0.1200 4.63 1.184 -0.1200 5.69 1.225 -0.1200 6.66 1.278 -0.1200 7.65 1.286 -0.1200 8.62 1.313 -0.1200 9.71 1.355 -0.1200 10.67 1.383 -0.1200 11.59 1.380 -0.1200 12.39 1.208 -0.1200 13.49 1.157 -0.1200 14.46 1.172 -0.1200 15.64 1.142 -0.1200 16.71 1.135 -0.1200 17.48 1.100 -0.1200 18.65 1.121 -0.1200 17.02 1.110 -0.1200 16.07 1.167 -0.1200 15.13 1.218 -0.1200 14.06 1.167 -0.1200 13.14 1.184 -0.1200 12.02 1.316 -0.1200 11.06 1.396 -0.1200 9.96 1.351 -0.1200 9.08 1.319 -0.1200 8.18 1.289 -0.1200 6.99 1.258 -0.1200 6.05 1.221 -0.1200 5.10 1.174 -0.1200 3.91 1.118 -0.1200 2.91 0.942 -0.1200 1.89 0.693 -0.1200 0.97 0.617 -0.1200 0.03 0.553 -0.1200 -1.16 0.440 -0.1200 -2.04 0.350 -0.1200 -3.20 0.254 -0.1200 -4.10 0.180 -0.1200 -5.23 0.075 -0.1200 -6.24 -0.028 -0.1200 Tabulated from data in file CL00745.DAT & reduced using program Q02.00L Average Reynolds #: 200100 Number of angles of attack: 49 alpha / Cl / Cm -6.10 0.207 -0.1200 -4.64 0.342 -0.1200 -3.77 0.430 -0.1200 -2.64 0.537 -0.1200 -1.52 0.637 -0.1200 -0.80 0.711 -0.1200 0.50 0.818 -0.1200 1.36 0.900 -0.1200 2.35 1.042 -0.1200 3.54 1.150 -0.1200 4.59 1.174 -0.1200 5.39 1.201 -0.1200 6.50 1.252 -0.1200 7.51 1.291 -0.1200 8.51 1.332 -0.1200 9.58 1.377 -0.1200 10.53 1.405 -0.1200 11.55 1.414 -0.1200 12.40 1.352 -0.1200 13.42 1.265 -0.1200 14.51 1.179 -0.1200 15.51 1.164 -0.1200 16.41 1.161 -0.1200 17.43 1.108 -0.1200 18.37 1.128 -0.1200 17.00 1.114 -0.1200 15.98 1.173 -0.1200 14.99 1.174 -0.1200 13.97 1.189 -0.1200 13.12 1.304 -0.1200 12.06 1.380 -0.1200 11.31 1.413 -0.1200 10.14 1.391 -0.1200 9.16 1.356 -0.1200 8.20 1.314 -0.1200 7.20 1.272 -0.1200 6.16 1.231 -0.1200 5.09 1.184 -0.1200 4.03 1.155 -0.1200 3.13 1.119 -0.1200 1.96 0.990 -0.1200 0.94 0.853 -0.1200 0.03 0.775 -0.1200 -0.97 0.682 -0.1200 -2.13 0.578 -0.1200 -3.10 0.489 -0.1200 -4.34 0.369 -0.1200 -5.38 0.265 -0.1200 -6.49 0.168 -0.1200 Tabulated from data in file CL00747.DAT & reduced using program Q02.00L Average Reynolds #: 299800 Number of angles of attack: 49 alpha / Cl / Cm -6.16 0.199 -0.1200 -4.82 0.357 -0.1200 -3.80 0.463 -0.1200 -2.88 0.559 -0.1200 -1.79 0.664 -0.1200 -0.77 0.760 -0.1200 0.29 0.863 -0.1200 1.44 0.973 -0.1200 2.39 1.080 -0.1200 3.53 1.124 -0.1200 4.45 1.146 -0.1200 5.65 1.199 -0.1200 6.43 1.238 -0.1200 7.41 1.289 -0.1200 8.51 1.346 -0.1200 9.65 1.396 -0.1200 10.52 1.422 -0.1200 11.59 1.433 -0.1200 12.24 1.420 -0.1200 13.38 1.309 -0.1200 14.40 1.221 -0.1200 15.30 1.188 -0.1200 16.30 1.121 -0.1200 17.27 1.128 -0.1200 18.22 1.149 -0.1200 17.14 1.120 -0.1200 16.12 1.140 -0.1200 15.15 1.190 -0.1200 14.09 1.253 -0.1200 13.23 1.317 -0.1200 12.16 1.415 -0.1200 11.03 1.428 -0.1200 10.04 1.407 -0.1200 8.94 1.363 -0.1200 8.04 1.321 -0.1200 7.01 1.265 -0.1200 5.96 1.210 -0.1200 4.96 1.161 -0.1200 4.05 1.129 -0.1200 3.04 1.103 -0.1200 2.02 1.036 -0.1200 1.04 0.932 -0.1200 -0.11 0.823 -0.1200 -1.05 0.732 -0.1200 -1.96 0.645 -0.1200 -3.07 0.537 -0.1200 -4.03 0.438 -0.1200 -5.06 0.328 -0.1200 -6.13 0.199 -0.1200 Tabulated from data in file CL00749.DAT & reduced using program Q02.00L File 7075atf1.lft created on 09-12-1997 at 13:46:18 using program FORMAT