Airfoil: S1223 Builder: Y. Tinel Comment: clean Number of Reynolds #'s: 8 Average Reynolds #: 61000 Number of angles of attack: 47 alpha / Cl / Cm -3.68 0.044 -0.2900 -2.28 0.649 -0.2900 -1.37 0.791 -0.2900 -0.17 0.913 -0.2900 0.67 0.988 -0.2900 1.94 1.084 -0.2900 2.85 1.123 -0.2900 3.70 1.058 -0.2900 4.54 0.961 -0.2900 5.96 0.996 -0.2900 6.90 0.968 -0.2900 7.87 0.996 -0.2900 8.80 1.011 -0.2900 9.74 1.032 -0.2900 10.53 1.046 -0.2900 11.92 1.033 -0.2900 12.85 1.121 -0.2900 13.64 1.129 -0.2900 14.64 1.214 -0.2900 15.63 1.207 -0.2900 16.59 1.260 -0.2900 18.00 1.342 -0.2900 18.96 1.354 -0.2900 19.96 1.391 -0.2900 18.66 1.326 -0.2900 17.38 1.268 -0.2900 16.58 1.231 -0.2900 15.41 1.185 -0.2900 14.68 1.153 -0.2900 13.59 1.129 -0.2900 12.58 1.107 -0.2900 11.62 1.069 -0.2900 10.62 1.062 -0.2900 9.41 1.051 -0.2900 8.38 1.003 -0.2900 7.62 0.965 -0.2900 6.65 0.943 -0.2900 5.39 0.978 -0.2900 4.45 1.012 -0.2900 3.44 1.156 -0.2900 2.46 1.095 -0.2900 1.63 1.053 -0.2900 0.47 0.965 -0.2900 -0.39 0.908 -0.2900 -1.37 0.807 -0.2900 -2.71 0.406 -0.2900 -3.73 0.058 -0.2900 Tabulated from data in file MS00132.DAT & reduced using program Q01.00L Average Reynolds #: 101600 Number of angles of attack: 53 alpha / Cl / Cm -6.82 -0.196 -0.2900 -5.71 -0.155 -0.2900 -4.53 0.003 -0.2900 -3.31 0.341 -0.2900 -2.47 0.727 -0.2900 -1.02 0.894 -0.2900 -0.04 0.996 -0.2900 0.89 1.085 -0.2900 1.76 1.167 -0.2900 2.61 1.246 -0.2900 3.73 1.332 -0.2900 4.81 1.421 -0.2900 5.75 1.487 -0.2900 6.66 1.544 -0.2900 8.03 1.149 -0.2900 8.63 1.135 -0.2900 9.61 1.151 -0.2900 11.07 1.155 -0.2900 12.00 1.188 -0.2900 12.94 1.176 -0.2900 13.88 1.261 -0.2900 14.94 1.245 -0.2900 15.89 1.244 -0.2900 16.84 1.235 -0.2900 18.01 1.278 -0.2900 19.05 1.359 -0.2900 19.66 1.353 -0.2900 18.54 1.344 -0.2900 17.33 1.304 -0.2900 16.19 1.209 -0.2900 15.57 1.223 -0.2900 14.32 1.223 -0.2900 13.59 1.197 -0.2900 12.57 1.208 -0.2900 11.34 1.161 -0.2900 10.33 1.128 -0.2900 9.32 1.144 -0.2900 8.29 1.120 -0.2900 7.52 1.208 -0.2900 6.64 1.530 -0.2900 5.38 1.451 -0.2900 4.70 1.392 -0.2900 3.33 1.280 -0.2900 2.42 1.209 -0.2900 1.50 1.119 -0.2900 0.48 1.023 -0.2900 -0.66 0.913 -0.2900 -1.77 0.791 -0.2900 -2.62 0.678 -0.2900 -3.71 0.197 -0.2900 -4.78 -0.038 -0.2900 -5.76 -0.180 -0.2900 -6.63 -0.220 -0.2900 Tabulated from data in file MS00133.DAT & reduced using program Q01.00L Average Reynolds #: 122600 Number of angles of attack: 65 alpha / Cl / Cm -8.72 -0.184 -0.2900 -7.84 -0.183 -0.2900 -6.88 -0.177 -0.2900 -5.84 -0.087 -0.2900 -4.85 0.042 -0.2900 -3.78 0.285 -0.2900 -2.63 0.752 -0.2900 -1.56 0.897 -0.2900 -0.60 0.998 -0.2900 0.42 1.103 -0.2900 1.53 1.204 -0.2900 2.57 1.297 -0.2900 3.63 1.376 -0.2900 4.55 1.448 -0.2900 5.55 1.517 -0.2900 6.63 1.591 -0.2900 7.69 1.651 -0.2900 8.61 1.668 -0.2900 9.45 1.122 -0.2900 10.43 1.149 -0.2900 11.43 1.189 -0.2900 12.55 1.186 -0.2900 13.60 1.266 -0.2900 14.50 1.223 -0.2900 15.54 1.241 -0.2900 16.53 1.267 -0.2900 17.56 1.310 -0.2900 18.59 1.338 -0.2900 19.51 1.393 -0.2900 20.59 1.402 -0.2900 21.57 1.480 -0.2900 22.58 1.500 -0.2900 23.52 1.501 -0.2900 22.69 1.460 -0.2900 21.68 1.473 -0.2900 20.73 1.393 -0.2900 19.73 1.367 -0.2900 18.72 1.318 -0.2900 17.70 1.284 -0.2900 16.68 1.283 -0.2900 15.65 1.268 -0.2900 14.69 1.227 -0.2900 13.69 1.225 -0.2900 12.63 1.199 -0.2900 11.67 1.160 -0.2900 10.63 1.143 -0.2900 9.60 1.102 -0.2900 8.65 1.116 -0.2900 7.65 1.114 -0.2900 6.67 1.179 -0.2900 5.78 1.536 -0.2900 4.69 1.449 -0.2900 3.69 1.371 -0.2900 2.65 1.292 -0.2900 1.68 1.201 -0.2900 0.61 1.102 -0.2900 -0.38 1.012 -0.2900 -1.39 0.898 -0.2900 -2.47 0.767 -0.2900 -3.51 0.345 -0.2900 -4.69 0.051 -0.2900 -5.74 -0.093 -0.2900 -6.75 -0.168 -0.2900 -7.66 -0.193 -0.2900 -8.71 -0.183 -0.2900 Tabulated from data in file MS00336.DAT & reduced using program Q01.00L Average Reynolds #: 147400 Number of angles of attack: 65 alpha / Cl / Cm -8.91 -0.167 -0.2900 -7.78 -0.159 -0.2900 -6.76 -0.115 -0.2900 -5.89 -0.056 -0.2900 -4.76 0.105 -0.2900 -3.70 0.330 -0.2900 -2.66 0.760 -0.2900 -1.54 0.905 -0.2900 -0.54 1.018 -0.2900 0.44 1.115 -0.2900 1.45 1.208 -0.2900 2.47 1.297 -0.2900 3.54 1.380 -0.2900 4.49 1.456 -0.2900 5.55 1.536 -0.2900 6.58 1.614 -0.2900 7.54 1.677 -0.2900 8.61 1.749 -0.2900 9.67 1.814 -0.2900 10.62 1.864 -0.2900 11.71 1.933 -0.2900 12.72 1.983 -0.2900 13.74 2.039 -0.2900 14.75 2.099 -0.2900 15.72 2.147 -0.2900 16.76 2.164 -0.2900 17.74 2.148 -0.2900 18.78 2.092 -0.2900 19.70 2.003 -0.2900 20.70 1.967 -0.2900 21.61 1.431 -0.2900 22.51 1.466 -0.2900 23.60 1.520 -0.2900 22.74 1.528 -0.2900 21.71 1.463 -0.2900 20.70 1.387 -0.2900 19.65 1.372 -0.2900 18.70 1.353 -0.2900 17.67 1.321 -0.2900 16.68 1.310 -0.2900 15.68 1.248 -0.2900 14.60 1.253 -0.2900 13.65 1.232 -0.2900 12.61 1.199 -0.2900 11.67 1.183 -0.2900 10.67 1.181 -0.2900 9.59 1.127 -0.2900 8.60 1.067 -0.2900 7.60 1.114 -0.2900 6.60 1.106 -0.2900 5.76 1.549 -0.2900 4.79 1.471 -0.2900 3.78 1.389 -0.2900 2.64 1.303 -0.2900 1.62 1.211 -0.2900 0.60 1.116 -0.2900 -0.47 1.012 -0.2900 -1.47 0.893 -0.2900 -2.49 0.769 -0.2900 -3.62 0.305 -0.2900 -4.58 0.119 -0.2900 -5.67 -0.030 -0.2900 -6.72 -0.129 -0.2900 -7.70 -0.171 -0.2900 -8.74 -0.179 -0.2900 Tabulated from data in file MS00337.DAT & reduced using program Q01.00L Average Reynolds #: 171400 Number of angles of attack: 65 alpha / Cl / Cm -8.86 -0.187 -0.2900 -7.85 -0.147 -0.2900 -6.88 -0.082 -0.2900 -5.82 0.021 -0.2900 -4.69 0.198 -0.2900 -3.65 0.336 -0.2900 -2.67 0.768 -0.2900 -1.40 0.923 -0.2900 -0.35 1.044 -0.2900 0.65 1.143 -0.2900 1.61 1.232 -0.2900 2.68 1.331 -0.2900 3.74 1.410 -0.2900 4.73 1.489 -0.2900 5.59 1.554 -0.2900 6.56 1.630 -0.2900 7.67 1.706 -0.2900 8.64 1.774 -0.2900 9.71 1.840 -0.2900 10.69 1.903 -0.2900 11.73 1.961 -0.2900 12.73 2.014 -0.2900 13.70 2.067 -0.2900 14.80 2.123 -0.2900 15.68 2.161 -0.2900 16.78 2.175 -0.2900 17.72 2.140 -0.2900 18.77 2.066 -0.2900 19.72 2.009 -0.2900 20.70 1.957 -0.2900 21.67 1.931 -0.2900 22.22 1.464 -0.2900 23.59 1.539 -0.2900 22.61 1.490 -0.2900 21.56 1.455 -0.2900 20.48 1.406 -0.2900 19.50 1.363 -0.2900 18.42 1.341 -0.2900 17.36 1.328 -0.2900 16.39 1.349 -0.2900 15.38 1.259 -0.2900 14.54 1.273 -0.2900 13.49 1.248 -0.2900 12.49 1.212 -0.2900 11.46 1.171 -0.2900 10.39 1.154 -0.2900 9.47 1.135 -0.2900 8.55 1.128 -0.2900 7.44 1.143 -0.2900 6.73 1.640 -0.2900 5.85 1.573 -0.2900 4.72 1.481 -0.2900 3.59 1.389 -0.2900 2.62 1.312 -0.2900 1.51 1.212 -0.2900 0.51 1.117 -0.2900 -0.57 1.006 -0.2900 -1.60 0.887 -0.2900 -2.52 0.781 -0.2900 -3.53 0.339 -0.2900 -4.55 0.188 -0.2900 -5.60 0.036 -0.2900 -6.67 -0.068 -0.2900 -7.70 -0.150 -0.2900 -8.76 -0.179 -0.2900 Tabulated from data in file MS00338.DAT & reduced using program Q01.00L Average Reynolds #: 198100 Number of angles of attack: 65 alpha / Cl / Cm -8.91 -0.167 -0.2900 -7.85 -0.150 -0.2900 -6.84 -0.054 -0.2900 -5.85 0.057 -0.2900 -4.73 0.211 -0.2900 -3.56 0.356 -0.2900 -2.83 0.753 -0.2900 -1.64 0.896 -0.2900 -0.56 1.021 -0.2900 0.48 1.127 -0.2900 1.43 1.215 -0.2900 2.52 1.317 -0.2900 3.51 1.401 -0.2900 4.63 1.487 -0.2900 5.80 1.580 -0.2900 6.62 1.642 -0.2900 7.73 1.726 -0.2900 8.60 1.785 -0.2900 9.68 1.855 -0.2900 10.75 1.928 -0.2900 11.66 1.979 -0.2900 12.64 2.033 -0.2900 13.68 2.086 -0.2900 14.69 2.143 -0.2900 15.80 2.181 -0.2900 16.70 2.183 -0.2900 17.73 2.137 -0.2900 18.70 2.055 -0.2900 19.62 1.995 -0.2900 20.67 1.984 -0.2900 21.60 1.941 -0.2900 22.63 1.910 -0.2900 23.61 1.889 -0.2900 22.76 1.911 -0.2900 21.80 1.932 -0.2900 20.86 1.973 -0.2900 19.77 1.991 -0.2900 18.82 2.050 -0.2900 17.93 2.125 -0.2900 16.93 2.188 -0.2900 15.85 2.187 -0.2900 14.85 2.156 -0.2900 13.91 2.111 -0.2900 12.76 2.047 -0.2900 11.86 1.995 -0.2900 10.82 1.924 -0.2900 9.75 1.855 -0.2900 8.76 1.785 -0.2900 7.73 1.717 -0.2900 6.69 1.640 -0.2900 5.63 1.559 -0.2900 4.43 1.462 -0.2900 3.68 1.404 -0.2900 2.58 1.311 -0.2900 1.57 1.218 -0.2900 0.64 1.129 -0.2900 -0.48 1.019 -0.2900 -1.42 0.908 -0.2900 -2.56 0.783 -0.2900 -3.51 0.349 -0.2900 -4.60 0.216 -0.2900 -5.64 0.073 -0.2900 -6.64 -0.052 -0.2900 -7.66 -0.149 -0.2900 -8.71 -0.175 -0.2900 Tabulated from data in file MS00339.DAT & reduced using program Q01.00L Average Reynolds #: 251900 Number of angles of attack: 65 alpha / Cl / Cm -8.87 -0.173 -0.2900 -7.84 -0.135 -0.2900 -6.81 -0.071 -0.2900 -5.77 0.014 -0.2900 -4.66 0.184 -0.2900 -3.57 0.339 -0.2900 -2.74 0.606 -0.2900 -1.60 0.882 -0.2900 -0.59 0.998 -0.2900 0.47 1.116 -0.2900 1.41 1.205 -0.2900 2.51 1.310 -0.2900 3.51 1.403 -0.2900 4.49 1.477 -0.2900 5.51 1.561 -0.2900 6.47 1.637 -0.2900 7.50 1.714 -0.2900 8.55 1.791 -0.2900 9.49 1.859 -0.2900 10.70 1.939 -0.2900 11.83 2.006 -0.2900 12.88 2.070 -0.2900 14.00 2.131 -0.2900 14.92 2.171 -0.2900 15.91 2.196 -0.2900 16.90 2.179 -0.2900 17.87 2.076 -0.2900 18.80 2.028 -0.2900 19.93 1.965 -0.2900 20.82 1.946 -0.2900 21.76 1.926 -0.2900 22.56 1.916 -0.2900 23.55 1.906 -0.2900 22.80 1.914 -0.2900 21.66 1.927 -0.2900 20.78 1.947 -0.2900 19.79 1.986 -0.2900 18.82 2.016 -0.2900 17.80 2.090 -0.2900 16.89 2.173 -0.2900 15.89 2.199 -0.2900 14.94 2.179 -0.2900 13.89 2.134 -0.2900 12.85 2.075 -0.2900 11.66 2.000 -0.2900 10.55 1.924 -0.2900 9.69 1.867 -0.2900 8.69 1.791 -0.2900 7.72 1.719 -0.2900 6.77 1.648 -0.2900 5.76 1.569 -0.2900 4.67 1.479 -0.2900 3.68 1.400 -0.2900 2.62 1.302 -0.2900 1.63 1.207 -0.2900 0.56 1.104 -0.2900 -0.48 0.985 -0.2900 -1.50 0.870 -0.2900 -2.51 0.755 -0.2900 -3.61 0.314 -0.2900 -4.60 0.182 -0.2900 -5.60 0.026 -0.2900 -6.68 -0.069 -0.2900 -7.70 -0.123 -0.2900 -8.73 -0.168 -0.2900 Tabulated from data in file MS00592.DAT & reduced using program Q01.00L Average Reynolds #: 302200 Number of angles of attack: 65 alpha / Cl / Cm -8.83 -0.132 -0.2900 -7.54 -0.065 -0.2900 -6.60 -0.008 -0.2900 -5.51 0.087 -0.2900 -4.47 0.221 -0.2900 -3.49 0.389 -0.2900 -2.66 0.753 -0.2900 -1.60 0.896 -0.2900 -0.53 1.016 -0.2900 0.49 1.129 -0.2900 1.50 1.227 -0.2900 2.54 1.327 -0.2900 3.58 1.424 -0.2900 4.57 1.506 -0.2900 5.62 1.588 -0.2900 6.63 1.672 -0.2900 7.65 1.748 -0.2900 8.63 1.824 -0.2900 9.67 1.900 -0.2900 10.70 1.970 -0.2900 11.71 2.034 -0.2900 12.77 2.099 -0.2900 13.79 2.152 -0.2900 15.10 2.199 -0.2900 16.24 2.210 -0.2900 17.12 2.155 -0.2900 18.20 2.043 -0.2900 18.89 2.012 -0.2900 19.85 1.964 -0.2900 20.84 1.948 -0.2900 21.73 1.904 -0.2900 22.67 1.905 -0.2900 23.72 1.921 -0.2900 22.54 1.895 -0.2900 21.45 1.923 -0.2900 20.49 1.951 -0.2900 19.37 1.966 -0.2900 18.27 2.034 -0.2900 17.59 2.086 -0.2900 16.69 2.183 -0.2900 15.62 2.212 -0.2900 14.60 2.196 -0.2900 13.40 2.138 -0.2900 12.33 2.074 -0.2900 11.40 2.011 -0.2900 10.50 1.949 -0.2900 9.67 1.888 -0.2900 8.58 1.808 -0.2900 7.61 1.731 -0.2900 6.67 1.658 -0.2900 5.62 1.573 -0.2900 4.56 1.485 -0.2900 3.58 1.403 -0.2900 2.56 1.307 -0.2900 1.55 1.208 -0.2900 0.51 1.109 -0.2900 -0.52 0.988 -0.2900 -1.52 0.873 -0.2900 -2.56 0.715 -0.2900 -3.75 0.308 -0.2900 -4.99 0.123 -0.2900 -5.88 0.026 -0.2900 -6.84 -0.029 -0.2900 -7.74 -0.088 -0.2900 -8.81 -0.134 -0.2900 Tabulated from data in file JG00595.DAT & reduced using program Q01.00L File s1223.lft created on 12-05-1997 at 15:25:51 using program FORMAT