Airfoil: S7075 (B) Builder: J. Robertson Comment: 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 -6.34 -0.358 -0.0800 -4.74 -0.245 -0.0800 -3.99 -0.195 -0.0800 -2.76 -0.099 -0.0800 -1.82 -0.026 -0.0800 -0.89 0.059 -0.0800 0.29 0.171 -0.0800 1.22 0.299 -0.0800 2.17 0.459 -0.0800 3.39 0.616 -0.0800 4.43 0.709 -0.0800 5.42 0.788 -0.0800 6.42 0.870 -0.0800 7.45 0.952 -0.0800 8.40 1.007 -0.0800 9.37 1.065 -0.0800 10.58 1.123 -0.0800 11.49 1.145 -0.0800 12.36 1.010 -0.0800 13.49 0.919 -0.0800 14.46 0.934 -0.0800 15.44 0.939 -0.0800 16.43 0.969 -0.0800 17.51 0.987 -0.0800 18.49 1.028 -0.0800 16.90 1.001 -0.0800 15.82 1.004 -0.0800 14.72 0.947 -0.0800 13.88 0.939 -0.0800 12.80 0.953 -0.0800 12.00 1.165 -0.0800 10.99 1.147 -0.0800 9.91 1.107 -0.0800 8.88 1.046 -0.0800 7.83 0.982 -0.0800 6.74 0.905 -0.0800 5.92 0.843 -0.0800 4.81 0.751 -0.0800 3.72 0.653 -0.0800 2.73 0.547 -0.0800 1.69 0.394 -0.0800 0.66 0.231 -0.0800 -0.34 0.116 -0.0800 -1.32 0.025 -0.0800 -2.33 -0.057 -0.0800 -3.37 -0.146 -0.0800 -4.43 -0.222 -0.0800 -5.46 -0.293 -0.0800 -6.50 -0.373 -0.0800 Tabulated from data in file CL00936.DAT & reduced using program Q02.00L Average Reynolds #: 100400 Number of angles of attack: 49 alpha / Cl / Cm -6.37 -0.374 -0.0800 -4.89 -0.202 -0.0800 -3.90 -0.107 -0.0800 -2.94 -0.021 -0.0800 -1.72 0.065 -0.0800 -0.79 0.125 -0.0800 0.17 0.260 -0.0800 1.38 0.419 -0.0800 2.37 0.520 -0.0800 3.34 0.604 -0.0800 4.48 0.709 -0.0800 5.23 0.772 -0.0800 6.55 0.889 -0.0800 7.54 0.963 -0.0800 8.52 1.024 -0.0800 9.46 1.079 -0.0800 10.38 1.125 -0.0800 11.56 1.154 -0.0800 12.43 1.156 -0.0800 13.53 0.974 -0.0800 14.36 0.955 -0.0800 15.45 0.988 -0.0800 16.42 0.959 -0.0800 17.57 0.945 -0.0800 18.32 0.956 -0.0800 16.87 0.941 -0.0800 15.72 0.961 -0.0800 14.89 0.921 -0.0800 13.77 0.961 -0.0800 12.86 0.983 -0.0800 11.88 1.163 -0.0800 10.77 1.134 -0.0800 9.90 1.098 -0.0800 8.82 1.033 -0.0800 7.70 0.964 -0.0800 6.85 0.902 -0.0800 5.71 0.804 -0.0800 4.86 0.729 -0.0800 3.72 0.623 -0.0800 2.63 0.526 -0.0800 1.83 0.451 -0.0800 0.72 0.322 -0.0800 -0.53 0.151 -0.0800 -1.30 0.073 -0.0800 -2.57 -0.000 -0.0800 -3.39 -0.069 -0.0800 -4.43 -0.166 -0.0800 -5.56 -0.271 -0.0800 -6.40 -0.370 -0.0800 Tabulated from data in file CL00938.DAT & reduced using program Q02.00L Average Reynolds #: 200800 Number of angles of attack: 49 alpha / Cl / Cm -6.07 -0.345 -0.0800 -4.87 -0.208 -0.0800 -3.76 -0.108 -0.0800 -2.76 -0.014 -0.0800 -1.68 0.090 -0.0800 -0.88 0.165 -0.0800 0.18 0.286 -0.0800 1.22 0.392 -0.0800 2.39 0.510 -0.0800 3.38 0.616 -0.0800 4.40 0.711 -0.0800 5.45 0.810 -0.0800 6.49 0.903 -0.0800 7.48 0.978 -0.0800 8.49 1.048 -0.0800 9.50 1.117 -0.0800 10.43 1.165 -0.0800 11.35 1.185 -0.0800 12.49 1.180 -0.0800 13.36 1.170 -0.0800 14.18 1.049 -0.0800 15.40 0.993 -0.0800 16.58 0.986 -0.0800 17.50 0.983 -0.0800 18.58 0.968 -0.0800 16.70 0.968 -0.0800 15.67 0.997 -0.0800 14.69 1.103 -0.0800 14.00 1.075 -0.0800 13.03 1.176 -0.0800 11.90 1.186 -0.0800 10.91 1.176 -0.0800 9.79 1.126 -0.0800 8.73 1.057 -0.0800 7.90 0.997 -0.0800 6.78 0.915 -0.0800 5.68 0.819 -0.0800 4.84 0.740 -0.0800 3.62 0.626 -0.0800 2.78 0.539 -0.0800 1.55 0.414 -0.0800 0.64 0.326 -0.0800 -0.47 0.201 -0.0800 -1.40 0.111 -0.0800 -2.36 0.017 -0.0800 -3.61 -0.099 -0.0800 -4.55 -0.186 -0.0800 -5.55 -0.278 -0.0800 -6.37 -0.381 -0.0800 Tabulated from data in file CL00940.DAT & reduced using program Q02.00L Average Reynolds #: 301600 Number of angles of attack: 49 alpha / Cl / Cm -6.49 -0.399 -0.0800 -4.89 -0.217 -0.0800 -3.74 -0.107 -0.0800 -2.79 -0.018 -0.0800 -1.51 0.107 -0.0800 -0.72 0.186 -0.0800 0.19 0.275 -0.0800 1.50 0.419 -0.0800 2.35 0.510 -0.0800 3.47 0.628 -0.0800 4.29 0.708 -0.0800 5.35 0.809 -0.0800 6.40 0.903 -0.0800 7.43 0.985 -0.0800 8.44 1.064 -0.0800 9.45 1.138 -0.0800 10.43 1.195 -0.0800 11.64 1.219 -0.0800 12.51 1.219 -0.0800 13.35 1.208 -0.0800 14.31 1.145 -0.0800 15.43 1.088 -0.0800 16.40 1.063 -0.0800 17.46 1.019 -0.0800 18.28 0.998 -0.0800 16.69 1.042 -0.0800 15.75 1.088 -0.0800 14.64 1.116 -0.0800 13.94 1.178 -0.0800 12.80 1.214 -0.0800 11.77 1.217 -0.0800 10.85 1.204 -0.0800 9.84 1.159 -0.0800 8.72 1.080 -0.0800 7.91 1.018 -0.0800 6.74 0.924 -0.0800 5.82 0.845 -0.0800 4.71 0.741 -0.0800 3.73 0.646 -0.0800 2.76 0.546 -0.0800 1.74 0.436 -0.0800 0.49 0.304 -0.0800 -0.52 0.196 -0.0800 -1.27 0.128 -0.0800 -2.38 0.019 -0.0800 -3.46 -0.085 -0.0800 -4.57 -0.191 -0.0800 -5.72 -0.301 -0.0800 -6.58 -0.409 -0.0800 Tabulated from data in file CL00942.DAT & reduced using program Q02.00L File 7075bt2.lft created on 09-12-1997 at 13:46:18 using program FORMAT