Moment data in the file is meaningless. mss 3-20-98 :::::::::::::: A18.LFT :::::::::::::: Airfoil: A18 Builder: R. Cooney Comment: clean Number of Reynolds #'s: 6 Average Reynolds #: 30500 Number of angles of attack: 49 alpha / Cl / Cm -5.44 -0.361 -0.0800 -4.15 -0.255 -0.0800 -2.90 -0.140 -0.0800 -1.98 -0.062 -0.0800 -1.08 0.021 -0.0800 0.12 0.140 -0.0800 0.95 0.225 -0.0800 2.16 0.329 -0.0800 3.18 0.449 -0.0800 4.03 0.552 -0.0800 5.24 0.697 -0.0800 6.34 0.863 -0.0800 7.17 0.961 -0.0800 8.34 1.037 -0.0800 9.23 1.082 -0.0800 10.40 1.086 -0.0800 11.23 1.032 -0.0800 12.37 1.028 -0.0800 13.18 0.928 -0.0800 14.28 0.834 -0.0800 15.09 0.843 -0.0800 16.23 0.878 -0.0800 17.40 0.990 -0.0800 18.28 1.078 -0.0800 19.18 0.998 -0.0800 17.75 0.989 -0.0800 16.86 0.926 -0.0800 15.79 0.877 -0.0800 14.75 0.877 -0.0800 13.89 0.854 -0.0800 12.87 0.904 -0.0800 11.88 1.083 -0.0800 10.86 1.124 -0.0800 10.03 1.103 -0.0800 9.01 1.058 -0.0800 7.94 1.003 -0.0800 6.97 0.960 -0.0800 5.96 0.827 -0.0800 4.90 0.710 -0.0800 3.87 0.562 -0.0800 2.85 0.452 -0.0800 1.77 0.348 -0.0800 0.78 0.267 -0.0800 -0.27 0.161 -0.0800 -1.42 0.040 -0.0800 -2.28 -0.040 -0.0800 -3.43 -0.143 -0.0800 -4.43 -0.244 -0.0800 -5.36 -0.335 -0.0800 Tabulated from data in file AB00520.DAT & reduced using program Q01.00L Average Reynolds #: 40300 Number of angles of attack: 49 alpha / Cl / Cm -5.15 -0.328 -0.0800 -4.08 -0.216 -0.0800 -2.95 -0.109 -0.0800 -2.15 -0.040 -0.0800 -1.00 0.064 -0.0800 0.09 0.176 -0.0800 1.09 0.271 -0.0800 2.12 0.396 -0.0800 3.20 0.532 -0.0800 4.19 0.687 -0.0800 5.27 0.819 -0.0800 6.34 0.921 -0.0800 7.32 0.986 -0.0800 8.35 1.026 -0.0800 9.33 1.070 -0.0800 10.14 1.093 -0.0800 11.20 1.132 -0.0800 12.26 1.096 -0.0800 13.28 0.981 -0.0800 14.25 0.899 -0.0800 15.27 0.903 -0.0800 16.30 0.916 -0.0800 17.29 0.951 -0.0800 18.37 0.971 -0.0800 19.16 1.029 -0.0800 17.80 0.981 -0.0800 16.82 0.950 -0.0800 15.84 0.913 -0.0800 14.87 0.921 -0.0800 13.93 0.907 -0.0800 12.86 0.957 -0.0800 11.97 1.142 -0.0800 10.92 1.137 -0.0800 9.98 1.105 -0.0800 8.95 1.076 -0.0800 7.91 1.038 -0.0800 6.89 0.976 -0.0800 5.83 0.905 -0.0800 4.78 0.799 -0.0800 3.81 0.673 -0.0800 2.82 0.511 -0.0800 1.80 0.384 -0.0800 0.64 0.266 -0.0800 -0.39 0.167 -0.0800 -1.42 0.062 -0.0800 -2.34 -0.021 -0.0800 -3.36 -0.112 -0.0800 -4.44 -0.218 -0.0800 -5.44 -0.310 -0.0800 Tabulated from data in file AB00519.DAT & reduced using program Q01.00L Average Reynolds #: 61000 Number of angles of attack: 33 alpha / Cl / Cm -5.24 -0.278 -0.0800 -3.34 -0.084 -0.0800 -2.01 0.030 -0.0800 -0.11 0.225 -0.0800 1.24 0.411 -0.0800 2.49 0.585 -0.0800 4.10 0.788 -0.0800 5.98 0.942 -0.0800 7.17 1.018 -0.0800 9.09 1.115 -0.0800 10.35 1.165 -0.0800 12.13 1.175 -0.0800 13.35 1.138 -0.0800 15.04 1.195 -0.0800 16.23 1.029 -0.0800 18.07 1.069 -0.0800 19.25 1.038 -0.0800 16.99 1.020 -0.0800 15.86 1.067 -0.0800 14.17 1.163 -0.0800 13.02 1.119 -0.0800 11.02 1.164 -0.0800 9.89 1.133 -0.0800 8.24 1.049 -0.0800 6.62 0.969 -0.0800 5.42 0.881 -0.0800 3.67 0.723 -0.0800 1.91 0.485 -0.0800 0.79 0.330 -0.0800 -0.73 0.142 -0.0800 -2.34 -0.006 -0.0800 -3.83 -0.133 -0.0800 -5.45 -0.303 -0.0800 Tabulated from data in file JG00160.DAT & reduced using program Q01.00L Average Reynolds #: 101700 Number of angles of attack: 33 alpha / Cl / Cm -5.36 -0.326 -0.0800 -3.51 -0.101 -0.0800 -1.61 0.093 -0.0800 -0.41 0.268 -0.0800 1.19 0.484 -0.0800 2.81 0.656 -0.0800 4.42 0.800 -0.0800 5.92 0.926 -0.0800 7.53 1.022 -0.0800 9.05 1.110 -0.0800 10.23 1.147 -0.0800 11.96 1.163 -0.0800 13.04 1.143 -0.0800 14.70 1.125 -0.0800 16.43 1.103 -0.0800 17.98 0.940 -0.0800 19.24 1.002 -0.0800 17.05 0.961 -0.0800 15.95 1.123 -0.0800 14.47 1.128 -0.0800 12.87 1.151 -0.0800 11.34 1.151 -0.0800 9.89 1.121 -0.0800 8.27 1.045 -0.0800 6.69 0.954 -0.0800 5.15 0.842 -0.0800 3.70 0.718 -0.0800 2.19 0.577 -0.0800 0.69 0.401 -0.0800 -0.75 0.202 -0.0800 -2.41 -0.018 -0.0800 -3.79 -0.144 -0.0800 -5.45 -0.341 -0.0800 Tabulated from data in file MS00162.DAT & reduced using program Q01.00L Average Reynolds #: 202700 Number of angles of attack: 33 alpha / Cl / Cm -5.40 -0.344 -0.0800 -3.56 -0.060 -0.0800 -1.46 0.209 -0.0800 0.08 0.374 -0.0800 1.49 0.519 -0.0800 2.86 0.656 -0.0800 4.31 0.794 -0.0800 5.63 0.899 -0.0800 7.57 1.039 -0.0800 8.88 1.118 -0.0800 10.12 1.168 -0.0800 11.88 1.184 -0.0800 13.33 1.212 -0.0800 14.88 1.180 -0.0800 16.51 1.141 -0.0800 17.60 1.181 -0.0800 19.11 1.102 -0.0800 17.14 1.187 -0.0800 15.79 1.186 -0.0800 14.17 1.194 -0.0800 12.61 1.223 -0.0800 11.27 1.181 -0.0800 9.81 1.157 -0.0800 8.19 1.072 -0.0800 6.51 0.953 -0.0800 5.30 0.865 -0.0800 3.38 0.697 -0.0800 2.08 0.570 -0.0800 0.63 0.424 -0.0800 -1.30 0.219 -0.0800 -2.68 0.037 -0.0800 -3.95 -0.120 -0.0800 -5.82 -0.397 -0.0800 Tabulated from data in file MS00164.DAT & reduced using program Q01.00L Average Reynolds #: 303200 Number of angles of attack: 33 alpha / Cl / Cm -5.37 -0.255 -0.0800 -3.59 -0.010 -0.0800 -2.33 0.132 -0.0800 -0.50 0.321 -0.0800 1.00 0.476 -0.0800 2.34 0.607 -0.0800 4.45 0.799 -0.0800 5.73 0.895 -0.0800 7.88 1.059 -0.0800 9.39 1.151 -0.0800 10.20 1.181 -0.0800 11.99 1.197 -0.0800 13.33 1.228 -0.0800 14.49 1.221 -0.0800 16.01 1.193 -0.0800 17.28 1.180 -0.0800 18.86 1.100 -0.0800 17.40 1.182 -0.0800 15.80 1.181 -0.0800 14.40 1.222 -0.0800 13.12 1.200 -0.0800 11.15 1.196 -0.0800 9.87 1.166 -0.0800 8.19 1.076 -0.0800 6.27 0.936 -0.0800 4.70 0.814 -0.0800 3.35 0.696 -0.0800 2.05 0.571 -0.0800 0.23 0.380 -0.0800 -0.90 0.266 -0.0800 -2.42 0.109 -0.0800 -3.99 -0.072 -0.0800 -5.34 -0.281 -0.0800 Tabulated from data in file MS00166.DAT & reduced using program Q01.00L File a18.lft created on 12-05-1997 at 15:25:49 using program FORMAT :::::::::::::: BE50.LFT :::::::::::::: Airfoil: BE50 Builder: R. Cooney Comment: clean Number of Reynolds #'s: 6 Average Reynolds #: 30600 Number of angles of attack: 49 alpha / Cl / Cm -5.03 -0.294 -0.1140 -3.92 -0.184 -0.1140 -2.96 -0.096 -0.1140 -1.81 -0.005 -0.1140 -0.86 0.087 -0.1140 0.27 0.190 -0.1140 1.20 0.282 -0.1140 2.35 0.418 -0.1140 3.30 0.588 -0.1140 4.43 0.730 -0.1140 5.38 0.801 -0.1140 6.31 0.853 -0.1140 7.47 0.909 -0.1140 8.44 0.947 -0.1140 9.37 0.936 -0.1140 10.26 0.924 -0.1140 11.36 0.955 -0.1140 12.46 0.903 -0.1140 13.37 0.963 -0.1140 14.47 0.911 -0.1140 15.38 0.901 -0.1140 16.29 0.924 -0.1140 17.45 1.016 -0.1140 18.41 1.046 -0.1140 19.36 1.100 -0.1140 18.01 0.976 -0.1140 17.10 0.986 -0.1140 16.09 0.899 -0.1140 14.92 0.887 -0.1140 14.04 0.848 -0.1140 12.90 0.861 -0.1140 11.97 0.874 -0.1140 10.82 0.877 -0.1140 9.95 0.915 -0.1140 9.05 0.855 -0.1140 7.96 0.914 -0.1140 7.12 0.855 -0.1140 6.02 0.832 -0.1140 4.95 0.775 -0.1140 3.91 0.664 -0.1140 2.94 0.528 -0.1140 1.87 0.381 -0.1140 0.75 0.257 -0.1140 -0.12 0.176 -0.1140 -1.23 0.074 -0.1140 -2.36 -0.030 -0.1140 -3.22 -0.106 -0.1140 -4.28 -0.209 -0.1140 -5.20 -0.301 -0.1140 Tabulated from data in file JG00567.DAT & reduced using program Q01.00L Average Reynolds #: 40100 Number of angles of attack: 49 alpha / Cl / Cm -5.02 -0.278 -0.1140 -3.78 -0.144 -0.1140 -2.79 -0.055 -0.1140 -1.78 0.034 -0.1140 -0.83 0.125 -0.1140 0.28 0.231 -0.1140 1.22 0.312 -0.1140 2.36 0.522 -0.1140 3.30 0.663 -0.1140 4.44 0.752 -0.1140 5.38 0.815 -0.1140 6.32 0.895 -0.1140 7.46 0.984 -0.1140 8.42 1.032 -0.1140 9.33 1.059 -0.1140 10.46 1.048 -0.1140 11.33 1.008 -0.1140 12.44 0.978 -0.1140 13.27 0.943 -0.1140 14.37 0.978 -0.1140 15.45 0.977 -0.1140 16.34 0.996 -0.1140 17.45 0.967 -0.1140 18.37 0.978 -0.1140 19.56 1.009 -0.1140 18.03 1.008 -0.1140 17.14 0.999 -0.1140 15.97 0.973 -0.1140 15.11 0.940 -0.1140 13.94 0.909 -0.1140 12.88 0.957 -0.1140 12.10 0.984 -0.1140 10.96 1.032 -0.1140 10.17 1.147 -0.1140 9.00 1.078 -0.1140 8.01 1.003 -0.1140 6.99 0.929 -0.1140 6.01 0.863 -0.1140 5.04 0.793 -0.1140 4.03 0.713 -0.1140 3.03 0.617 -0.1140 2.03 0.470 -0.1140 0.98 0.291 -0.1140 -0.26 0.184 -0.1140 -1.22 0.091 -0.1140 -2.17 0.014 -0.1140 -3.18 -0.069 -0.1140 -4.20 -0.168 -0.1140 -5.28 -0.272 -0.1140 Tabulated from data in file JG00568.DAT & reduced using program Q01.00L Average Reynolds #: 62200 Number of angles of attack: 33 alpha / Cl / Cm -4.98 -0.243 -0.1140 -3.40 -0.084 -0.1140 -1.73 0.057 -0.1140 -0.21 0.193 -0.1140 1.40 0.445 -0.1140 2.94 0.600 -0.1140 4.47 0.738 -0.1140 5.74 0.848 -0.1140 7.42 0.982 -0.1140 8.97 1.090 -0.1140 10.57 1.195 -0.1140 12.02 1.223 -0.1140 13.46 1.112 -0.1140 14.82 1.125 -0.1140 16.40 1.119 -0.1140 17.95 1.047 -0.1140 19.54 1.023 -0.1140 17.50 1.078 -0.1140 15.94 1.083 -0.1140 14.55 1.142 -0.1140 12.96 1.118 -0.1140 11.64 1.186 -0.1140 9.94 1.155 -0.1140 8.53 1.045 -0.1140 7.06 0.934 -0.1140 5.54 0.808 -0.1140 3.96 0.675 -0.1140 2.49 0.546 -0.1140 0.82 0.332 -0.1140 -0.73 0.103 -0.1140 -2.34 -0.040 -0.1140 -3.71 -0.143 -0.1140 -5.24 -0.310 -0.1140 Tabulated from data in file JG00569.DAT & reduced using program Q01.00L Average Reynolds #: 101700 Number of angles of attack: 33 alpha / Cl / Cm -5.06 -0.303 -0.1140 -3.44 -0.117 -0.1140 -1.72 0.026 -0.1140 -0.34 0.230 -0.1140 1.38 0.453 -0.1140 2.97 0.600 -0.1140 4.27 0.715 -0.1140 6.03 0.870 -0.1140 7.28 0.973 -0.1140 9.10 1.118 -0.1140 10.42 1.183 -0.1140 12.06 1.202 -0.1140 13.50 1.187 -0.1140 14.77 1.080 -0.1140 16.34 1.042 -0.1140 17.87 1.015 -0.1140 19.51 0.990 -0.1140 17.33 1.012 -0.1140 16.00 1.047 -0.1140 14.55 1.112 -0.1140 13.10 1.181 -0.1140 11.57 1.188 -0.1140 10.02 1.161 -0.1140 8.61 1.063 -0.1140 6.97 0.929 -0.1140 5.40 0.797 -0.1140 4.00 0.673 -0.1140 2.50 0.539 -0.1140 0.81 0.371 -0.1140 -0.69 0.166 -0.1140 -2.19 -0.016 -0.1140 -3.71 -0.141 -0.1140 -5.29 -0.329 -0.1140 Tabulated from data in file JG00571.DAT & reduced using program Q01.00L Average Reynolds #: 202800 Number of angles of attack: 33 alpha / Cl / Cm -5.37 -0.351 -0.1140 -3.31 -0.097 -0.1140 -1.77 0.105 -0.1140 -0.32 0.265 -0.1140 1.27 0.431 -0.1140 2.73 0.579 -0.1140 4.41 0.742 -0.1140 5.77 0.870 -0.1140 7.55 1.023 -0.1140 8.79 1.117 -0.1140 10.35 1.197 -0.1140 11.90 1.217 -0.1140 13.40 1.186 -0.1140 14.80 1.196 -0.1140 16.23 1.083 -0.1140 17.81 1.030 -0.1140 19.21 0.989 -0.1140 17.17 1.049 -0.1140 15.85 1.105 -0.1140 14.52 1.154 -0.1140 13.13 1.192 -0.1140 11.65 1.216 -0.1140 9.92 1.175 -0.1140 8.57 1.096 -0.1140 6.95 0.960 -0.1140 5.34 0.816 -0.1140 4.02 0.690 -0.1140 2.19 0.508 -0.1140 0.59 0.347 -0.1140 -0.97 0.182 -0.1140 -2.39 0.013 -0.1140 -3.83 -0.156 -0.1140 -5.27 -0.348 -0.1140 Tabulated from data in file JG00573.DAT & reduced using program Q01.00L Average Reynolds #: 303900 Number of angles of attack: 33 alpha / Cl / Cm -5.04 -0.301 -0.1140 -3.50 -0.087 -0.1140 -2.11 0.082 -0.1140 -0.35 0.260 -0.1140 1.20 0.421 -0.1140 2.95 0.597 -0.1140 4.42 0.739 -0.1140 6.17 0.907 -0.1140 7.67 1.043 -0.1140 9.27 1.155 -0.1140 10.55 1.219 -0.1140 11.88 1.233 -0.1140 13.45 1.193 -0.1140 14.90 1.170 -0.1140 16.04 1.150 -0.1140 17.64 1.049 -0.1140 19.11 0.984 -0.1140 17.63 1.059 -0.1140 16.14 1.124 -0.1140 14.84 1.161 -0.1140 12.84 1.207 -0.1140 11.63 1.231 -0.1140 9.96 1.189 -0.1140 8.49 1.099 -0.1140 7.01 0.979 -0.1140 5.30 0.820 -0.1140 3.63 0.654 -0.1140 2.00 0.491 -0.1140 0.56 0.336 -0.1140 -0.83 0.201 -0.1140 -2.33 0.045 -0.1140 -3.82 -0.137 -0.1140 -5.43 -0.363 -0.1140 Tabulated from data in file JG00575.DAT & reduced using program Q01.00L File be50.lft created on 12-05-1997 at 15:25:49 using program FORMAT :::::::::::::: CH10T.LFT :::::::::::::: Airfoil: CH 10-48-13 Builder: C. Hollinger Comment: plain trip @ x/c = 40% (h/c = 0.2%; w/c = 0.9%) Number of Reynolds #'s: 5 Average Reynolds #: 99400 Number of angles of attack: 65 alpha / Cl / Cm -3.94 0.222 -0.2300 -2.99 0.270 -0.2300 -1.96 0.391 -0.2300 -0.99 0.577 -0.2300 0.12 0.780 -0.2300 1.10 0.884 -0.2300 2.12 0.984 -0.2300 3.06 1.064 -0.2300 4.15 1.151 -0.2300 5.15 1.254 -0.2300 6.24 1.351 -0.2300 7.21 1.440 -0.2300 8.07 0.804 -0.2300 9.08 0.877 -0.2300 10.08 0.870 -0.2300 11.11 0.916 -0.2300 12.09 0.956 -0.2300 13.11 1.020 -0.2300 14.12 1.060 -0.2300 15.17 1.124 -0.2300 16.13 1.151 -0.2300 17.16 1.189 -0.2300 18.13 1.186 -0.2300 19.18 1.272 -0.2300 20.28 1.796 -0.2300 21.31 1.742 -0.2300 22.26 1.683 -0.2300 23.31 1.711 -0.2300 24.26 1.711 -0.2300 25.30 1.706 -0.2300 26.21 1.527 -0.2300 27.25 1.498 -0.2300 28.23 1.505 -0.2300 27.31 1.475 -0.2300 26.37 1.555 -0.2300 25.48 1.712 -0.2300 24.43 1.713 -0.2300 23.46 1.687 -0.2300 22.46 1.685 -0.2300 21.46 1.735 -0.2300 20.50 1.780 -0.2300 19.46 1.835 -0.2300 18.48 1.946 -0.2300 17.54 2.014 -0.2300 16.49 1.993 -0.2300 15.25 1.109 -0.2300 14.28 1.064 -0.2300 13.27 1.046 -0.2300 12.29 0.999 -0.2300 11.25 0.955 -0.2300 10.27 0.926 -0.2300 9.33 0.889 -0.2300 8.24 0.816 -0.2300 7.28 0.832 -0.2300 6.30 0.873 -0.2300 5.28 0.834 -0.2300 4.28 0.836 -0.2300 3.35 1.079 -0.2300 2.37 0.992 -0.2300 1.16 0.881 -0.2300 0.28 0.789 -0.2300 -0.82 0.603 -0.2300 -1.84 0.389 -0.2300 -2.89 0.269 -0.2300 -3.90 0.203 -0.2300 Tabulated from data in file MS00340.DAT & reduced using program Q01.00L Average Reynolds #: 126700 Number of angles of attack: 43 alpha / Cl / Cm -3.98 0.209 -0.2300 -2.27 0.331 -0.2300 -0.58 0.665 -0.2300 0.88 0.883 -0.2300 2.41 1.032 -0.2300 3.90 1.152 -0.2300 5.57 1.291 -0.2300 7.04 1.409 -0.2300 8.39 0.867 -0.2300 10.00 0.904 -0.2300 11.25 0.967 -0.2300 12.99 1.028 -0.2300 14.52 1.085 -0.2300 15.97 1.144 -0.2300 17.62 1.219 -0.2300 18.97 1.243 -0.2300 20.70 1.727 -0.2300 22.16 1.668 -0.2300 23.69 1.719 -0.2300 25.21 1.698 -0.2300 26.54 1.532 -0.2300 28.28 1.500 -0.2300 25.98 1.714 -0.2300 24.63 1.736 -0.2300 23.17 1.687 -0.2300 21.70 1.684 -0.2300 20.24 1.766 -0.2300 18.66 1.866 -0.2300 17.29 1.960 -0.2300 15.56 1.966 -0.2300 13.93 1.040 -0.2300 12.45 1.019 -0.2300 11.02 0.949 -0.2300 9.31 0.896 -0.2300 7.95 0.860 -0.2300 6.51 0.856 -0.2300 5.01 0.893 -0.2300 3.46 1.117 -0.2300 2.06 0.989 -0.2300 0.41 0.821 -0.2300 -1.21 0.482 -0.2300 -2.77 0.255 -0.2300 -4.10 0.190 -0.2300 Tabulated from data in file JG00557.DAT & reduced using program Q01.00L Average Reynolds #: 151800 Number of angles of attack: 43 alpha / Cl / Cm -3.80 0.206 -0.2300 -2.12 0.349 -0.2300 -0.88 0.581 -0.2300 1.02 0.899 -0.2300 2.51 1.045 -0.2300 4.07 1.170 -0.2300 5.54 1.292 -0.2300 7.11 1.427 -0.2300 8.73 1.566 -0.2300 10.01 0.914 -0.2300 11.33 0.965 -0.2300 12.98 1.035 -0.2300 14.51 1.075 -0.2300 16.04 1.138 -0.2300 17.65 1.940 -0.2300 19.18 1.815 -0.2300 20.69 1.719 -0.2300 22.17 1.671 -0.2300 23.54 1.717 -0.2300 25.26 1.714 -0.2300 26.30 1.526 -0.2300 27.73 1.496 -0.2300 26.11 1.535 -0.2300 24.60 1.726 -0.2300 23.05 1.733 -0.2300 21.70 1.675 -0.2300 20.21 1.747 -0.2300 18.76 1.855 -0.2300 17.19 1.964 -0.2300 15.71 2.015 -0.2300 14.19 1.906 -0.2300 12.37 1.009 -0.2300 10.82 0.938 -0.2300 9.34 0.897 -0.2300 7.94 0.866 -0.2300 6.15 0.834 -0.2300 4.71 0.874 -0.2300 3.44 1.115 -0.2300 1.94 0.978 -0.2300 0.25 0.799 -0.2300 -1.19 0.494 -0.2300 -2.90 0.261 -0.2300 -4.12 0.194 -0.2300 Tabulated from data in file JG00558.DAT & reduced using program Q01.00L Average Reynolds #: 176500 Number of angles of attack: 43 alpha / Cl / Cm -3.89 0.186 -0.2300 -2.26 0.319 -0.2300 -0.78 0.612 -0.2300 0.91 0.891 -0.2300 2.21 1.020 -0.2300 3.74 1.149 -0.2300 5.55 1.299 -0.2300 6.81 1.408 -0.2300 8.52 1.561 -0.2300 10.26 1.703 -0.2300 11.65 1.800 -0.2300 13.16 1.907 -0.2300 14.78 1.988 -0.2300 16.26 2.003 -0.2300 17.67 1.913 -0.2300 19.26 1.786 -0.2300 20.69 1.705 -0.2300 22.23 1.684 -0.2300 23.76 1.709 -0.2300 25.31 1.736 -0.2300 26.44 1.508 -0.2300 27.67 1.493 -0.2300 26.24 1.711 -0.2300 24.39 1.730 -0.2300 22.99 1.703 -0.2300 21.56 1.684 -0.2300 20.16 1.732 -0.2300 18.63 1.837 -0.2300 17.22 1.952 -0.2300 15.69 2.032 -0.2300 14.03 1.963 -0.2300 12.60 1.865 -0.2300 10.90 1.743 -0.2300 9.26 1.614 -0.2300 8.00 1.503 -0.2300 6.47 1.364 -0.2300 4.98 1.232 -0.2300 3.18 1.089 -0.2300 1.79 0.960 -0.2300 0.40 0.815 -0.2300 -1.21 0.446 -0.2300 -2.96 0.235 -0.2300 -4.26 0.178 -0.2300 Tabulated from data in file PG00559.DAT & reduced using program Q01.00L Average Reynolds #: 201200 Number of angles of attack: 53 alpha / Cl / Cm -2.09 0.375 -0.2300 -1.02 0.620 -0.2300 0.15 0.832 -0.2300 1.26 0.947 -0.2300 2.33 1.047 -0.2300 3.40 1.143 -0.2300 4.12 1.195 -0.2300 5.15 1.287 -0.2300 6.30 1.392 -0.2300 7.26 1.479 -0.2300 8.60 1.597 -0.2300 9.51 1.676 -0.2300 10.61 1.770 -0.2300 11.62 1.846 -0.2300 12.65 1.923 -0.2300 13.68 1.977 -0.2300 14.72 1.999 -0.2300 15.91 2.009 -0.2300 16.58 1.964 -0.2300 17.67 1.886 -0.2300 19.04 1.768 -0.2300 19.67 1.729 -0.2300 20.89 1.671 -0.2300 21.39 1.665 -0.2300 22.53 1.693 -0.2300 23.84 1.707 -0.2300 24.36 1.740 -0.2300 22.94 1.719 -0.2300 21.53 1.691 -0.2300 20.93 1.670 -0.2300 20.19 1.704 -0.2300 19.09 1.768 -0.2300 17.66 1.886 -0.2300 17.11 1.928 -0.2300 15.72 2.010 -0.2300 15.12 2.019 -0.2300 13.51 1.967 -0.2300 13.42 1.967 -0.2300 12.00 1.871 -0.2300 10.65 1.767 -0.2300 10.03 1.710 -0.2300 8.67 1.596 -0.2300 7.88 1.528 -0.2300 7.10 1.461 -0.2300 5.79 1.341 -0.2300 5.01 1.267 -0.2300 3.87 1.165 -0.2300 2.77 1.075 -0.2300 2.06 1.006 -0.2300 0.98 0.902 -0.2300 -0.24 0.768 -0.2300 -1.29 0.510 -0.2300 -2.46 0.307 -0.2300 Tabulated from data in file MS00155.DAT & reduced using program Q01.00L File ch10t.lft created on 12-05-1997 at 15:25:49 using program FORMAT :::::::::::::: E374B.LFT :::::::::::::: Airfoil: E374 (B) Builder: M. Bame Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 61300 Number of angles of attack: 49 alpha / Cl / Cm -6.58 -0.407 -0.0420 -5.25 -0.348 -0.0420 -4.17 -0.282 -0.0420 -3.14 -0.209 -0.0420 -2.29 -0.120 -0.0420 -1.25 0.014 -0.0420 -0.22 0.150 -0.0420 1.00 0.284 -0.0420 1.82 0.347 -0.0420 2.86 0.427 -0.0420 3.89 0.544 -0.0420 4.92 0.697 -0.0420 5.97 0.793 -0.0420 7.01 0.881 -0.0420 8.06 0.960 -0.0420 9.10 0.983 -0.0420 10.08 1.036 -0.0420 11.14 1.056 -0.0420 12.04 1.062 -0.0420 13.10 1.057 -0.0420 14.02 1.079 -0.0420 15.13 1.041 -0.0420 16.14 0.946 -0.0420 17.13 0.909 -0.0420 18.16 0.925 -0.0420 16.93 0.887 -0.0420 15.90 0.982 -0.0420 14.97 1.026 -0.0420 14.00 1.067 -0.0420 12.97 1.054 -0.0420 11.90 1.071 -0.0420 10.94 1.048 -0.0420 9.90 1.008 -0.0420 8.91 0.976 -0.0420 7.91 0.951 -0.0420 6.92 0.875 -0.0420 5.86 0.783 -0.0420 4.88 0.686 -0.0420 3.82 0.551 -0.0420 2.81 0.432 -0.0420 1.76 0.354 -0.0420 0.71 0.254 -0.0420 -0.26 0.142 -0.0420 -1.30 -0.006 -0.0420 -2.33 -0.122 -0.0420 -3.34 -0.216 -0.0420 -4.36 -0.290 -0.0420 -5.38 -0.349 -0.0420 -6.45 -0.402 -0.0420 Tabulated from data in file JG00361.DAT & reduced using program Q01.00L Average Reynolds #: 102100 Number of angles of attack: 49 alpha / Cl / Cm -6.36 -0.418 -0.0420 -5.21 -0.362 -0.0420 -4.20 -0.251 -0.0420 -3.17 -0.128 -0.0420 -2.24 0.022 -0.0420 -1.23 0.156 -0.0420 -0.14 0.261 -0.0420 0.85 0.332 -0.0420 1.85 0.411 -0.0420 2.84 0.501 -0.0420 3.89 0.602 -0.0420 5.01 0.710 -0.0420 6.02 0.805 -0.0420 7.01 0.895 -0.0420 8.03 0.939 -0.0420 9.13 0.975 -0.0420 10.03 1.010 -0.0420 11.00 1.037 -0.0420 12.07 1.052 -0.0420 12.98 1.031 -0.0420 14.08 1.011 -0.0420 15.03 0.914 -0.0420 16.12 0.889 -0.0420 17.12 0.868 -0.0420 18.10 0.864 -0.0420 16.92 0.871 -0.0420 15.85 0.887 -0.0420 14.94 0.915 -0.0420 13.98 1.028 -0.0420 12.95 1.044 -0.0420 11.90 1.036 -0.0420 10.91 1.024 -0.0420 9.96 0.994 -0.0420 8.89 0.953 -0.0420 7.95 0.925 -0.0420 6.91 0.875 -0.0420 5.91 0.784 -0.0420 4.86 0.681 -0.0420 3.88 0.586 -0.0420 2.80 0.481 -0.0420 1.80 0.395 -0.0420 0.81 0.313 -0.0420 -0.26 0.235 -0.0420 -1.26 0.139 -0.0420 -2.34 -0.007 -0.0420 -3.39 -0.154 -0.0420 -4.38 -0.278 -0.0420 -5.47 -0.382 -0.0420 -6.44 -0.425 -0.0420 Tabulated from data in file JG00363.DAT & reduced using program Q01.00L Average Reynolds #: 152900 Number of angles of attack: 53 alpha / Cl / Cm -6.53 -0.461 -0.0420 -5.31 -0.370 -0.0420 -4.32 -0.225 -0.0420 -3.14 -0.090 -0.0420 -2.19 -0.024 -0.0420 -1.12 0.084 -0.0420 -0.22 0.236 -0.0420 0.82 0.327 -0.0420 1.85 0.418 -0.0420 2.89 0.514 -0.0420 3.98 0.619 -0.0420 4.92 0.713 -0.0420 5.95 0.809 -0.0420 7.05 0.902 -0.0420 8.00 0.938 -0.0420 9.00 0.976 -0.0420 10.02 1.009 -0.0420 10.98 1.036 -0.0420 12.00 1.049 -0.0420 13.03 1.072 -0.0420 14.11 1.038 -0.0420 15.05 0.932 -0.0420 15.98 0.895 -0.0420 17.00 0.887 -0.0420 18.04 0.879 -0.0420 19.10 0.874 -0.0420 20.13 0.897 -0.0420 18.84 0.876 -0.0420 17.84 0.864 -0.0420 16.91 0.886 -0.0420 15.89 0.918 -0.0420 14.92 0.931 -0.0420 13.94 1.034 -0.0420 12.97 1.082 -0.0420 11.94 1.050 -0.0420 10.91 1.033 -0.0420 9.98 1.007 -0.0420 8.91 0.967 -0.0420 7.92 0.930 -0.0420 6.95 0.887 -0.0420 5.87 0.790 -0.0420 4.82 0.692 -0.0420 3.76 0.587 -0.0420 2.82 0.495 -0.0420 1.77 0.399 -0.0420 0.71 0.308 -0.0420 -0.28 0.221 -0.0420 -1.37 0.040 -0.0420 -2.32 -0.043 -0.0420 -3.45 -0.130 -0.0420 -4.35 -0.241 -0.0420 -5.50 -0.397 -0.0420 -6.47 -0.462 -0.0420 Tabulated from data in file AB00501.DAT & reduced using program Q01.00L Average Reynolds #: 203500 Number of angles of attack: 49 alpha / Cl / Cm -6.15 -0.385 -0.0420 -5.30 -0.268 -0.0420 -3.99 -0.135 -0.0420 -3.06 -0.066 -0.0420 -2.14 0.002 -0.0420 -1.12 0.097 -0.0420 -0.22 0.248 -0.0420 0.89 0.349 -0.0420 1.99 0.448 -0.0420 2.89 0.533 -0.0420 3.94 0.634 -0.0420 4.98 0.735 -0.0420 5.99 0.827 -0.0420 6.95 0.898 -0.0420 8.02 0.940 -0.0420 9.06 0.983 -0.0420 9.99 1.017 -0.0420 11.06 1.041 -0.0420 11.99 1.058 -0.0420 13.05 1.084 -0.0420 14.13 1.033 -0.0420 15.12 0.938 -0.0420 15.99 0.917 -0.0420 17.06 0.891 -0.0420 18.29 0.850 -0.0420 16.76 0.907 -0.0420 15.73 0.915 -0.0420 14.82 0.984 -0.0420 13.92 1.067 -0.0420 12.88 1.083 -0.0420 11.95 1.052 -0.0420 10.96 1.033 -0.0420 9.91 1.008 -0.0420 8.89 0.969 -0.0420 7.90 0.927 -0.0420 6.86 0.885 -0.0420 5.86 0.807 -0.0420 4.86 0.714 -0.0420 3.86 0.617 -0.0420 2.83 0.519 -0.0420 1.80 0.420 -0.0420 0.71 0.321 -0.0420 -0.30 0.216 -0.0420 -1.29 0.073 -0.0420 -2.38 -0.028 -0.0420 -3.44 -0.103 -0.0420 -4.42 -0.180 -0.0420 -5.60 -0.326 -0.0420 -6.53 -0.439 -0.0420 Tabulated from data in file JG00359.DAT & reduced using program Q01.00L Average Reynolds #: 305000 Number of angles of attack: 49 alpha / Cl / Cm -6.37 -0.361 -0.0420 -5.24 -0.244 -0.0420 -4.08 -0.154 -0.0420 -3.09 -0.075 -0.0420 -2.13 0.002 -0.0420 -1.02 0.093 -0.0420 -0.00 0.215 -0.0420 1.00 0.356 -0.0420 2.06 0.454 -0.0420 2.97 0.540 -0.0420 3.96 0.635 -0.0420 5.16 0.752 -0.0420 6.09 0.831 -0.0420 6.96 0.881 -0.0420 8.01 0.932 -0.0420 9.10 0.982 -0.0420 10.06 1.017 -0.0420 11.07 1.041 -0.0420 12.03 1.117 -0.0420 13.02 1.104 -0.0420 14.07 1.092 -0.0420 15.00 1.004 -0.0420 16.02 0.934 -0.0420 17.06 0.904 -0.0420 18.08 0.892 -0.0420 16.82 0.909 -0.0420 15.73 0.942 -0.0420 14.85 1.015 -0.0420 13.75 1.110 -0.0420 12.94 1.094 -0.0420 11.90 1.097 -0.0420 10.91 1.032 -0.0420 9.91 1.006 -0.0420 8.86 0.965 -0.0420 7.82 0.915 -0.0420 6.78 0.867 -0.0420 5.78 0.794 -0.0420 4.79 0.701 -0.0420 3.75 0.601 -0.0420 2.70 0.498 -0.0420 1.61 0.396 -0.0420 0.60 0.299 -0.0420 -0.41 0.138 -0.0420 -1.48 0.044 -0.0420 -2.53 -0.041 -0.0420 -3.45 -0.117 -0.0420 -4.66 -0.212 -0.0420 -5.60 -0.293 -0.0420 -6.78 -0.429 -0.0420 Tabulated from data in file JG00062.DAT & reduced using program Q01.00L File e374b.lft created on 12-05-1997 at 15:25:49 using program FORMAT :::::::::::::: E387A.LFT :::::::::::::: Airfoil: E387 (A) Builder: B. Champine Comment: clean Number of Reynolds #'s: 8 Average Reynolds #: 30100 Number of angles of attack: 97 alpha / Cl / Cm -6.79 -0.351 -0.0850 -6.45 -0.328 -0.0850 -5.81 -0.275 -0.0850 -5.43 -0.243 -0.0850 -4.85 -0.200 -0.0850 -4.46 -0.178 -0.0850 -3.91 -0.140 -0.0850 -3.44 -0.110 -0.0850 -2.73 -0.058 -0.0850 -2.43 -0.032 -0.0850 -1.75 0.026 -0.0850 -1.36 0.065 -0.0850 -0.78 0.114 -0.0850 -0.38 0.152 -0.0850 0.20 0.215 -0.0850 0.71 0.269 -0.0850 1.31 0.325 -0.0850 1.64 0.363 -0.0850 2.33 0.428 -0.0850 2.72 0.461 -0.0850 3.30 0.512 -0.0850 3.74 0.551 -0.0850 4.27 0.570 -0.0850 4.76 0.615 -0.0850 5.43 0.646 -0.0850 5.78 0.662 -0.0850 6.44 0.728 -0.0850 6.76 0.717 -0.0850 7.33 0.714 -0.0850 7.81 0.766 -0.0850 8.35 0.808 -0.0850 8.80 0.794 -0.0850 9.44 0.830 -0.0850 9.81 0.867 -0.0850 10.33 0.889 -0.0850 10.90 1.141 -0.0850 11.56 1.239 -0.0850 11.94 1.234 -0.0850 12.49 1.248 -0.0850 12.92 1.204 -0.0850 13.37 1.230 -0.0850 13.94 1.269 -0.0850 14.35 1.268 -0.0850 14.87 1.051 -0.0850 15.49 1.081 -0.0850 15.88 1.056 -0.0850 16.48 1.069 -0.0850 16.88 1.039 -0.0850 17.52 1.062 -0.0850 17.08 1.046 -0.0850 16.50 1.067 -0.0850 15.95 1.078 -0.0850 15.47 1.088 -0.0850 14.95 1.062 -0.0850 14.57 1.060 -0.0850 14.08 1.091 -0.0850 13.63 1.160 -0.0850 13.06 1.232 -0.0850 12.62 1.228 -0.0850 12.06 1.218 -0.0850 11.63 1.210 -0.0850 11.06 1.222 -0.0850 10.59 1.204 -0.0850 10.05 1.182 -0.0850 9.57 1.023 -0.0850 8.94 0.813 -0.0850 8.56 0.793 -0.0850 7.97 0.770 -0.0850 7.52 0.770 -0.0850 6.94 0.747 -0.0850 6.51 0.741 -0.0850 5.96 0.688 -0.0850 5.28 0.664 -0.0850 4.85 0.638 -0.0850 4.40 0.619 -0.0850 3.82 0.579 -0.0850 3.48 0.552 -0.0850 2.99 0.505 -0.0850 2.35 0.460 -0.0850 1.88 0.395 -0.0850 1.43 0.373 -0.0850 0.89 0.307 -0.0850 0.34 0.257 -0.0850 -0.27 0.199 -0.0850 -0.66 0.167 -0.0850 -1.20 0.111 -0.0850 -1.66 0.068 -0.0850 -2.23 0.018 -0.0850 -2.72 -0.019 -0.0850 -3.20 -0.052 -0.0850 -3.71 -0.083 -0.0850 -4.21 -0.121 -0.0850 -4.72 -0.155 -0.0850 -5.21 -0.194 -0.0850 -5.80 -0.247 -0.0850 -6.40 -0.304 -0.0850 -6.79 -0.330 -0.0850 Tabulated from data in file MS00296.DAT & reduced using program Q01.00L Average Reynolds #: 40500 Number of angles of attack: 97 alpha / Cl / Cm -7.15 -0.381 -0.0850 -6.62 -0.348 -0.0850 -5.86 -0.288 -0.0850 -5.49 -0.256 -0.0850 -4.76 -0.198 -0.0850 -4.39 -0.170 -0.0850 -3.82 -0.125 -0.0850 -3.40 -0.090 -0.0850 -2.74 -0.036 -0.0850 -2.41 -0.010 -0.0850 -1.78 0.045 -0.0850 -1.38 0.084 -0.0850 -0.76 0.142 -0.0850 -0.37 0.184 -0.0850 0.24 0.260 -0.0850 0.66 0.314 -0.0850 1.29 0.387 -0.0850 1.72 0.451 -0.0850 2.35 0.510 -0.0850 2.75 0.539 -0.0850 3.40 0.579 -0.0850 3.72 0.583 -0.0850 4.29 0.587 -0.0850 4.77 0.611 -0.0850 5.28 0.649 -0.0850 5.83 0.670 -0.0850 6.36 0.701 -0.0850 6.75 0.727 -0.0850 7.48 0.732 -0.0850 7.76 0.742 -0.0850 8.30 1.067 -0.0850 8.93 1.139 -0.0850 9.42 1.163 -0.0850 9.88 1.181 -0.0850 10.44 1.189 -0.0850 10.94 1.192 -0.0850 11.45 1.191 -0.0850 11.91 1.186 -0.0850 12.42 1.177 -0.0850 12.89 1.191 -0.0850 13.54 1.098 -0.0850 13.89 1.101 -0.0850 14.48 1.104 -0.0850 14.89 1.115 -0.0850 15.57 1.073 -0.0850 15.83 1.055 -0.0850 16.40 1.014 -0.0850 16.87 1.039 -0.0850 17.50 1.041 -0.0850 16.96 1.008 -0.0850 16.43 1.029 -0.0850 15.96 1.029 -0.0850 15.54 1.062 -0.0850 14.99 1.070 -0.0850 14.57 1.059 -0.0850 13.98 1.095 -0.0850 13.60 1.216 -0.0850 13.07 1.205 -0.0850 12.64 1.206 -0.0850 12.03 1.195 -0.0850 11.63 1.196 -0.0850 11.02 1.192 -0.0850 10.63 1.200 -0.0850 10.10 1.189 -0.0850 9.61 1.174 -0.0850 9.06 1.153 -0.0850 8.63 1.132 -0.0850 8.06 1.075 -0.0850 7.59 0.863 -0.0850 6.95 0.724 -0.0850 6.54 0.702 -0.0850 5.95 0.681 -0.0850 5.42 0.649 -0.0850 4.87 0.625 -0.0850 4.51 0.608 -0.0850 3.86 0.609 -0.0850 3.47 0.582 -0.0850 2.81 0.541 -0.0850 2.42 0.529 -0.0850 1.94 0.478 -0.0850 1.41 0.418 -0.0850 0.92 0.360 -0.0850 0.40 0.302 -0.0850 -0.15 0.225 -0.0850 -0.69 0.167 -0.0850 -1.18 0.112 -0.0850 -1.70 0.065 -0.0850 -2.29 0.015 -0.0850 -2.66 -0.011 -0.0850 -3.31 -0.062 -0.0850 -3.68 -0.093 -0.0850 -4.22 -0.139 -0.0850 -4.73 -0.178 -0.0850 -5.32 -0.223 -0.0850 -5.75 -0.259 -0.0850 -6.27 -0.300 -0.0850 -6.81 -0.341 -0.0850 Tabulated from data in file MS00294.DAT & reduced using program Q01.00L Average Reynolds #: 50800 Number of angles of attack: 97 alpha / Cl / Cm -7.05 -0.367 -0.0850 -6.50 -0.335 -0.0850 -5.90 -0.288 -0.0850 -5.50 -0.254 -0.0850 -4.91 -0.206 -0.0850 -4.44 -0.177 -0.0850 -3.86 -0.140 -0.0850 -3.46 -0.107 -0.0850 -2.77 -0.041 -0.0850 -2.37 0.002 -0.0850 -1.81 0.047 -0.0850 -1.35 0.099 -0.0850 -0.77 0.179 -0.0850 -0.36 0.233 -0.0850 0.19 0.301 -0.0850 0.62 0.361 -0.0850 1.20 0.423 -0.0850 1.65 0.463 -0.0850 2.26 0.515 -0.0850 2.78 0.555 -0.0850 3.40 0.604 -0.0850 3.78 0.628 -0.0850 4.34 0.685 -0.0850 4.79 0.753 -0.0850 5.47 0.832 -0.0850 5.83 0.869 -0.0850 6.44 0.934 -0.0850 6.87 0.977 -0.0850 7.48 1.035 -0.0850 7.84 1.071 -0.0850 8.51 1.128 -0.0850 8.88 1.145 -0.0850 9.43 1.169 -0.0850 9.92 1.179 -0.0850 10.54 1.190 -0.0850 10.88 1.198 -0.0850 11.42 1.205 -0.0850 11.89 1.209 -0.0850 12.44 1.206 -0.0850 12.89 1.201 -0.0850 13.50 1.187 -0.0850 13.91 1.193 -0.0850 14.54 1.216 -0.0850 14.89 1.178 -0.0850 15.43 1.205 -0.0850 15.89 1.146 -0.0850 16.40 1.138 -0.0850 16.87 1.061 -0.0850 17.47 1.084 -0.0850 16.99 1.120 -0.0850 16.47 1.139 -0.0850 15.98 1.096 -0.0850 15.53 1.151 -0.0850 15.05 1.100 -0.0850 14.57 1.090 -0.0850 14.07 1.178 -0.0850 13.63 1.191 -0.0850 13.06 1.191 -0.0850 12.59 1.201 -0.0850 12.09 1.198 -0.0850 11.57 1.201 -0.0850 11.05 1.188 -0.0850 10.58 1.186 -0.0850 10.04 1.175 -0.0850 9.64 1.169 -0.0850 9.05 1.141 -0.0850 8.63 1.120 -0.0850 8.02 1.075 -0.0850 7.58 1.027 -0.0850 7.03 0.976 -0.0850 6.53 0.924 -0.0850 5.93 0.863 -0.0850 5.46 0.819 -0.0850 4.91 0.762 -0.0850 4.46 0.689 -0.0850 3.88 0.628 -0.0850 3.41 0.594 -0.0850 2.95 0.566 -0.0850 2.35 0.521 -0.0850 1.84 0.486 -0.0850 1.40 0.435 -0.0850 0.80 0.378 -0.0850 0.40 0.335 -0.0850 -0.23 0.239 -0.0850 -0.64 0.190 -0.0850 -1.25 0.115 -0.0850 -1.65 0.075 -0.0850 -2.21 0.021 -0.0850 -2.72 -0.030 -0.0850 -3.35 -0.088 -0.0850 -3.74 -0.116 -0.0850 -4.37 -0.161 -0.0850 -4.73 -0.192 -0.0850 -5.28 -0.227 -0.0850 -5.82 -0.267 -0.0850 -6.43 -0.330 -0.0850 -6.81 -0.351 -0.0850 Tabulated from data in file MS00295.DAT & reduced using program Q01.00L Average Reynolds #: 61300 Number of angles of attack: 33 alpha / Cl / Cm -7.00 -0.383 -0.0850 -5.32 -0.240 -0.0850 -3.76 -0.125 -0.0850 -2.08 0.053 -0.0850 -0.64 0.251 -0.0850 0.85 0.409 -0.0850 2.55 0.578 -0.0850 4.10 0.739 -0.0850 5.47 0.870 -0.0850 6.96 1.011 -0.0850 8.79 1.171 -0.0850 10.11 1.213 -0.0850 11.69 1.241 -0.0850 13.03 1.246 -0.0850 14.51 1.179 -0.0850 16.16 1.156 -0.0850 17.59 1.117 -0.0850 15.85 1.146 -0.0850 14.43 1.237 -0.0850 12.97 1.247 -0.0850 11.26 1.230 -0.0850 9.90 1.203 -0.0850 8.35 1.136 -0.0850 6.83 0.992 -0.0850 5.27 0.840 -0.0850 3.79 0.698 -0.0850 2.27 0.543 -0.0850 0.68 0.389 -0.0850 -1.00 0.174 -0.0850 -2.45 0.003 -0.0850 -3.93 -0.144 -0.0850 -5.50 -0.255 -0.0850 -7.10 -0.394 -0.0850 Tabulated from data in file AB00208.DAT & reduced using program Q01.00L Average Reynolds #: 101900 Number of angles of attack: 33 alpha / Cl / Cm -6.91 -0.398 -0.0850 -5.33 -0.269 -0.0850 -3.68 -0.067 -0.0850 -2.00 0.154 -0.0850 -0.51 0.306 -0.0850 0.78 0.428 -0.0850 2.49 0.589 -0.0850 3.91 0.723 -0.0850 5.56 0.877 -0.0850 6.91 1.009 -0.0850 8.65 1.149 -0.0850 10.07 1.178 -0.0850 11.69 1.202 -0.0850 13.05 1.202 -0.0850 14.68 1.178 -0.0850 15.96 1.060 -0.0850 17.66 1.036 -0.0850 15.81 1.079 -0.0850 14.25 1.193 -0.0850 12.99 1.186 -0.0850 11.44 1.189 -0.0850 9.96 1.161 -0.0850 8.29 1.111 -0.0850 6.84 0.982 -0.0850 5.20 0.825 -0.0850 3.73 0.683 -0.0850 2.03 0.519 -0.0850 0.58 0.381 -0.0850 -0.92 0.238 -0.0850 -2.47 0.074 -0.0850 -4.14 -0.155 -0.0850 -5.56 -0.310 -0.0850 -7.10 -0.420 -0.0850 Tabulated from data in file AB00210.DAT & reduced using program Q01.00L Average Reynolds #: 152600 Number of angles of attack: 33 alpha / Cl / Cm -7.07 -0.441 -0.0850 -5.32 -0.275 -0.0850 -3.53 -0.021 -0.0850 -2.08 0.116 -0.0850 -0.60 0.253 -0.0850 0.85 0.403 -0.0850 2.50 0.572 -0.0850 4.04 0.728 -0.0850 5.61 0.880 -0.0850 7.03 1.015 -0.0850 8.61 1.130 -0.0850 10.01 1.172 -0.0850 11.54 1.191 -0.0850 13.00 1.194 -0.0850 14.53 1.208 -0.0850 16.09 1.124 -0.0850 17.55 1.072 -0.0850 15.84 1.113 -0.0850 14.38 1.210 -0.0850 12.98 1.191 -0.0850 11.45 1.189 -0.0850 9.94 1.161 -0.0850 8.43 1.112 -0.0850 6.81 0.985 -0.0850 5.29 0.837 -0.0850 3.80 0.690 -0.0850 2.08 0.513 -0.0850 0.69 0.371 -0.0850 -0.93 0.203 -0.0850 -2.61 0.051 -0.0850 -4.05 -0.102 -0.0850 -5.62 -0.328 -0.0850 -7.26 -0.453 -0.0850 Tabulated from data in file JG00554.DAT & reduced using program Q01.00L Average Reynolds #: 203100 Number of angles of attack: 33 alpha / Cl / Cm -7.02 -0.429 -0.0850 -4.62 -0.122 -0.0850 -3.39 -0.001 -0.0850 -2.05 0.121 -0.0850 -0.39 0.282 -0.0850 1.18 0.443 -0.0850 2.71 0.601 -0.0850 4.30 0.767 -0.0850 5.65 0.900 -0.0850 7.21 1.045 -0.0850 8.76 1.136 -0.0850 10.20 1.180 -0.0850 11.53 1.192 -0.0850 13.06 1.198 -0.0850 14.59 1.225 -0.0850 16.50 1.092 -0.0850 17.67 1.057 -0.0850 15.68 1.145 -0.0850 14.13 1.222 -0.0850 12.89 1.196 -0.0850 11.29 1.186 -0.0850 9.79 1.166 -0.0850 8.19 1.103 -0.0850 6.68 0.992 -0.0850 4.98 0.825 -0.0850 3.56 0.682 -0.0850 1.74 0.493 -0.0850 0.42 0.356 -0.0850 -1.21 0.187 -0.0850 -2.73 0.048 -0.0850 -4.61 -0.135 -0.0850 -5.86 -0.315 -0.0850 -7.57 -0.470 -0.0850 Tabulated from data in file JG00212.DAT & reduced using program Q01.00L Average Reynolds #: 304400 Number of angles of attack: 33 alpha / Cl / Cm -6.95 -0.427 -0.0850 -5.49 -0.229 -0.0850 -3.97 -0.075 -0.0850 -2.28 0.085 -0.0850 -0.45 0.264 -0.0850 1.01 0.423 -0.0850 2.46 0.579 -0.0850 4.03 0.743 -0.0850 5.54 0.897 -0.0850 6.93 1.023 -0.0850 8.49 1.123 -0.0850 9.96 1.184 -0.0850 11.48 1.202 -0.0850 12.94 1.209 -0.0850 14.37 1.260 -0.0850 15.98 1.150 -0.0850 17.76 1.063 -0.0850 15.83 1.151 -0.0850 14.45 1.263 -0.0850 12.92 1.209 -0.0850 11.42 1.196 -0.0850 9.90 1.174 -0.0850 8.39 1.107 -0.0850 6.88 1.005 -0.0850 5.31 0.861 -0.0850 3.78 0.703 -0.0850 2.06 0.522 -0.0850 0.41 0.348 -0.0850 -1.41 0.157 -0.0850 -2.77 0.028 -0.0850 -4.21 -0.107 -0.0850 -5.50 -0.242 -0.0850 -7.09 -0.442 -0.0850 Tabulated from data in file JG00214.DAT & reduced using program Q01.00L File e387a.lft created on 12-05-1997 at 15:25:49 using program FORMAT :::::::::::::: FX63137B.LFT :::::::::::::: Airfoil: FX 63-137 (B) Builder: M. Allen Comment: clean Number of Reynolds #'s: 8 Average Reynolds #: 61500 Number of angles of attack: 53 alpha / Cl / Cm -6.11 -0.394 -0.1700 -4.63 -0.107 -0.1700 -3.60 0.049 -0.1700 -2.65 0.165 -0.1700 -1.67 0.272 -0.1700 -0.49 0.342 -0.1700 0.42 0.389 -0.1700 1.34 0.443 -0.1700 2.49 0.501 -0.1700 3.40 0.551 -0.1700 4.41 0.645 -0.1700 5.58 0.693 -0.1700 6.61 0.741 -0.1700 7.56 0.768 -0.1700 8.58 0.821 -0.1700 9.59 0.850 -0.1700 10.56 0.870 -0.1700 11.49 0.894 -0.1700 12.65 0.901 -0.1700 13.60 0.918 -0.1700 14.54 0.970 -0.1700 15.69 0.992 -0.1700 16.52 1.022 -0.1700 17.53 1.105 -0.1700 18.57 1.163 -0.1700 19.59 1.187 -0.1700 20.58 1.216 -0.1700 19.46 1.141 -0.1700 18.32 1.126 -0.1700 17.43 1.075 -0.1700 16.37 1.008 -0.1700 15.28 0.988 -0.1700 14.31 0.953 -0.1700 13.38 0.896 -0.1700 12.26 0.877 -0.1700 11.37 0.881 -0.1700 10.31 0.864 -0.1700 9.27 0.797 -0.1700 8.26 0.780 -0.1700 7.32 0.740 -0.1700 6.24 0.682 -0.1700 5.34 0.659 -0.1700 4.31 0.603 -0.1700 3.25 0.504 -0.1700 2.23 0.462 -0.1700 1.19 0.404 -0.1700 0.11 0.333 -0.1700 -0.87 0.279 -0.1700 -1.92 0.212 -0.1700 -2.95 0.100 -0.1700 -3.96 -0.028 -0.1700 -5.02 -0.206 -0.1700 -6.02 -0.433 -0.1700 Tabulated from data in file AB00504.DAT & reduced using program Q01.00L Average Reynolds #: 80400 Number of angles of attack: 65 alpha / Cl / Cm -8.04 -0.336 -0.1700 -6.99 -0.330 -0.1700 -6.06 -0.312 -0.1700 -5.03 -0.025 -0.1700 -4.00 0.123 -0.1700 -2.86 0.256 -0.1700 -1.79 0.345 -0.1700 -0.78 0.448 -0.1700 0.19 0.458 -0.1700 1.12 0.523 -0.1700 2.20 0.559 -0.1700 3.29 0.612 -0.1700 4.29 0.688 -0.1700 5.33 0.754 -0.1700 6.31 0.781 -0.1700 7.30 0.826 -0.1700 8.36 0.879 -0.1700 9.33 0.922 -0.1700 10.34 0.963 -0.1700 11.41 1.018 -0.1700 12.43 1.502 -0.1700 13.48 1.667 -0.1700 14.48 1.667 -0.1700 15.45 1.647 -0.1700 16.32 1.270 -0.1700 17.38 1.175 -0.1700 18.31 1.198 -0.1700 19.43 1.261 -0.1700 20.49 1.270 -0.1700 21.37 1.247 -0.1700 22.36 1.292 -0.1700 23.37 1.327 -0.1700 24.47 1.365 -0.1700 23.54 1.345 -0.1700 22.62 1.288 -0.1700 21.56 1.214 -0.1700 20.56 1.226 -0.1700 19.53 1.221 -0.1700 18.53 1.226 -0.1700 17.52 1.196 -0.1700 16.53 1.189 -0.1700 15.64 1.655 -0.1700 14.66 1.669 -0.1700 13.66 1.664 -0.1700 12.60 1.646 -0.1700 11.71 1.617 -0.1700 10.62 1.570 -0.1700 9.55 1.491 -0.1700 8.57 1.402 -0.1700 7.44 0.841 -0.1700 6.36 0.772 -0.1700 5.44 0.743 -0.1700 4.38 0.678 -0.1700 3.40 0.605 -0.1700 2.38 0.566 -0.1700 1.39 0.512 -0.1700 0.35 0.452 -0.1700 -0.67 0.410 -0.1700 -1.64 0.359 -0.1700 -2.69 0.249 -0.1700 -3.74 0.140 -0.1700 -4.76 -0.004 -0.1700 -5.83 -0.307 -0.1700 -6.85 -0.352 -0.1700 -7.89 -0.334 -0.1700 Tabulated from data in file MS00297.DAT & reduced using program Q01.00L Average Reynolds #: 89800 Number of angles of attack: 65 alpha / Cl / Cm -7.76 -0.317 -0.1700 -6.95 -0.338 -0.1700 -5.96 -0.286 -0.1700 -4.87 0.014 -0.1700 -3.93 0.159 -0.1700 -2.81 0.287 -0.1700 -1.79 0.364 -0.1700 -0.87 0.422 -0.1700 0.23 0.485 -0.1700 1.20 0.547 -0.1700 2.22 0.601 -0.1700 3.19 0.629 -0.1700 4.25 0.707 -0.1700 5.26 0.782 -0.1700 6.26 0.837 -0.1700 7.40 1.357 -0.1700 8.40 1.443 -0.1700 9.44 1.521 -0.1700 10.50 1.590 -0.1700 11.52 1.638 -0.1700 12.47 1.657 -0.1700 13.50 1.676 -0.1700 14.49 1.675 -0.1700 15.49 1.666 -0.1700 16.51 1.647 -0.1700 17.29 1.176 -0.1700 18.32 1.199 -0.1700 19.38 1.232 -0.1700 20.39 1.218 -0.1700 21.33 1.297 -0.1700 22.34 1.281 -0.1700 23.34 1.333 -0.1700 24.44 1.351 -0.1700 23.61 1.372 -0.1700 22.67 1.313 -0.1700 21.54 1.304 -0.1700 20.55 1.286 -0.1700 19.52 1.223 -0.1700 18.48 1.165 -0.1700 17.48 1.185 -0.1700 16.48 1.161 -0.1700 15.49 1.155 -0.1700 14.44 1.158 -0.1700 13.70 1.688 -0.1700 12.75 1.666 -0.1700 11.71 1.652 -0.1700 10.65 1.610 -0.1700 9.57 1.537 -0.1700 8.59 1.456 -0.1700 7.51 1.359 -0.1700 6.51 1.249 -0.1700 5.43 0.769 -0.1700 4.39 0.725 -0.1700 3.37 0.649 -0.1700 2.33 0.590 -0.1700 1.31 0.542 -0.1700 0.33 0.484 -0.1700 -0.69 0.430 -0.1700 -1.61 0.372 -0.1700 -2.57 0.304 -0.1700 -3.80 0.167 -0.1700 -4.77 0.031 -0.1700 -5.85 -0.290 -0.1700 -6.78 -0.333 -0.1700 -7.79 -0.337 -0.1700 Tabulated from data in file MS00299.DAT & reduced using program Q01.00L Average Reynolds #: 101700 Number of angles of attack: 53 alpha / Cl / Cm -5.95 -0.280 -0.1700 -5.04 -0.019 -0.1700 -3.72 0.165 -0.1700 -2.83 0.274 -0.1700 -1.75 0.399 -0.1700 -0.55 0.491 -0.1700 0.26 0.543 -0.1700 1.20 0.617 -0.1700 2.18 0.696 -0.1700 3.41 0.827 -0.1700 4.31 1.001 -0.1700 5.58 1.201 -0.1700 6.44 1.297 -0.1700 7.43 1.393 -0.1700 8.35 1.470 -0.1700 9.61 1.566 -0.1700 10.59 1.630 -0.1700 11.46 1.667 -0.1700 12.55 1.702 -0.1700 13.64 1.697 -0.1700 14.70 1.697 -0.1700 15.48 1.707 -0.1700 16.54 1.705 -0.1700 17.64 1.696 -0.1700 18.39 1.145 -0.1700 19.39 1.184 -0.1700 20.32 1.259 -0.1700 19.60 1.191 -0.1700 18.47 1.154 -0.1700 17.59 1.149 -0.1700 16.49 1.120 -0.1700 15.58 1.100 -0.1700 14.46 1.182 -0.1700 13.79 1.698 -0.1700 12.78 1.702 -0.1700 11.78 1.681 -0.1700 10.76 1.632 -0.1700 9.69 1.568 -0.1700 8.74 1.500 -0.1700 7.55 1.388 -0.1700 6.50 1.280 -0.1700 5.57 1.179 -0.1700 4.56 0.999 -0.1700 3.50 0.870 -0.1700 2.37 0.683 -0.1700 1.32 0.613 -0.1700 0.32 0.541 -0.1700 -0.61 0.473 -0.1700 -1.73 0.389 -0.1700 -2.65 0.289 -0.1700 -3.79 0.148 -0.1700 -4.55 0.045 -0.1700 -5.82 -0.278 -0.1700 Tabulated from data in file MS00158.DAT & reduced using program Q01.00L Average Reynolds #: 149500 Number of angles of attack: 65 alpha / Cl / Cm -8.04 -0.246 -0.1700 -6.87 -0.154 -0.1700 -5.82 0.078 -0.1700 -4.70 0.245 -0.1700 -3.76 0.356 -0.1700 -2.61 0.493 -0.1700 -1.53 0.596 -0.1700 -0.71 0.672 -0.1700 0.28 0.766 -0.1700 1.37 0.863 -0.1700 2.33 0.950 -0.1700 3.46 1.047 -0.1700 4.38 1.129 -0.1700 5.40 1.238 -0.1700 6.46 1.339 -0.1700 7.42 1.423 -0.1700 8.49 1.505 -0.1700 9.42 1.569 -0.1700 10.44 1.632 -0.1700 11.46 1.676 -0.1700 12.46 1.690 -0.1700 13.45 1.694 -0.1700 14.48 1.694 -0.1700 15.44 1.693 -0.1700 16.56 1.689 -0.1700 17.48 1.683 -0.1700 18.47 1.658 -0.1700 19.07 1.168 -0.1700 20.49 1.248 -0.1700 21.69 1.271 -0.1700 22.42 1.306 -0.1700 23.59 1.289 -0.1700 24.32 1.318 -0.1700 23.32 1.319 -0.1700 22.30 1.266 -0.1700 21.44 1.255 -0.1700 20.31 1.211 -0.1700 19.34 1.167 -0.1700 18.33 1.167 -0.1700 17.37 1.190 -0.1700 16.37 1.142 -0.1700 15.44 1.113 -0.1700 14.79 1.695 -0.1700 13.67 1.692 -0.1700 12.63 1.691 -0.1700 11.75 1.684 -0.1700 10.62 1.637 -0.1700 9.57 1.574 -0.1700 8.58 1.508 -0.1700 7.62 1.433 -0.1700 6.51 1.336 -0.1700 5.50 1.240 -0.1700 4.42 1.123 -0.1700 3.39 1.030 -0.1700 2.49 0.951 -0.1700 1.33 0.846 -0.1700 0.32 0.754 -0.1700 -0.71 0.657 -0.1700 -1.72 0.563 -0.1700 -2.77 0.461 -0.1700 -3.67 0.352 -0.1700 -4.88 0.204 -0.1700 -5.86 0.058 -0.1700 -6.74 -0.141 -0.1700 -7.83 -0.239 -0.1700 Tabulated from data in file MS00298.DAT & reduced using program Q01.00L Average Reynolds #: 202700 Number of angles of attack: 65 alpha / Cl / Cm -8.38 -0.233 -0.1700 -6.81 -0.089 -0.1700 -5.90 0.116 -0.1700 -4.88 0.244 -0.1700 -3.88 0.348 -0.1700 -2.87 0.460 -0.1700 -1.86 0.568 -0.1700 -0.83 0.668 -0.1700 0.28 0.775 -0.1700 1.25 0.867 -0.1700 2.31 0.972 -0.1700 3.29 1.068 -0.1700 4.39 1.172 -0.1700 5.36 1.253 -0.1700 6.47 1.358 -0.1700 7.60 1.452 -0.1700 8.71 1.538 -0.1700 9.72 1.603 -0.1700 10.76 1.660 -0.1700 11.71 1.696 -0.1700 12.64 1.705 -0.1700 13.68 1.712 -0.1700 14.67 1.720 -0.1700 15.69 1.726 -0.1700 16.69 1.723 -0.1700 17.67 1.712 -0.1700 18.72 1.691 -0.1700 19.76 1.677 -0.1700 20.63 1.667 -0.1700 21.25 1.250 -0.1700 22.35 1.259 -0.1700 23.35 1.331 -0.1700 24.40 1.345 -0.1700 23.45 1.316 -0.1700 22.45 1.322 -0.1700 21.46 1.254 -0.1700 20.45 1.217 -0.1700 19.44 1.207 -0.1700 18.44 1.148 -0.1700 17.41 1.133 -0.1700 16.47 1.150 -0.1700 15.46 1.158 -0.1700 14.72 1.719 -0.1700 13.55 1.708 -0.1700 12.57 1.703 -0.1700 11.56 1.691 -0.1700 10.45 1.642 -0.1700 9.48 1.587 -0.1700 8.27 1.505 -0.1700 7.23 1.419 -0.1700 6.17 1.324 -0.1700 5.31 1.240 -0.1700 4.39 1.159 -0.1700 3.40 1.063 -0.1700 2.33 0.961 -0.1700 1.30 0.859 -0.1700 0.38 0.768 -0.1700 -0.69 0.665 -0.1700 -1.70 0.567 -0.1700 -2.69 0.465 -0.1700 -3.77 0.346 -0.1700 -4.80 0.235 -0.1700 -5.82 0.107 -0.1700 -6.82 -0.108 -0.1700 -7.83 -0.204 -0.1700 Tabulated from data in file JG00507.DAT & reduced using program Q01.00L Average Reynolds #: 252800 Number of angles of attack: 65 alpha / Cl / Cm -8.04 -0.188 -0.1700 -6.99 -0.074 -0.1700 -5.89 0.132 -0.1700 -4.88 0.243 -0.1700 -3.86 0.353 -0.1700 -2.83 0.464 -0.1700 -1.79 0.579 -0.1700 -0.79 0.679 -0.1700 0.25 0.783 -0.1700 1.28 0.884 -0.1700 2.32 0.987 -0.1700 3.33 1.086 -0.1700 4.35 1.186 -0.1700 5.42 1.281 -0.1700 6.41 1.364 -0.1700 7.42 1.452 -0.1700 8.46 1.530 -0.1700 9.48 1.594 -0.1700 10.49 1.650 -0.1700 11.55 1.689 -0.1700 12.62 1.702 -0.1700 13.69 1.712 -0.1700 14.68 1.725 -0.1700 15.67 1.736 -0.1700 16.79 1.729 -0.1700 17.67 1.728 -0.1700 18.71 1.720 -0.1700 19.68 1.698 -0.1700 20.66 1.684 -0.1700 21.54 1.668 -0.1700 22.45 1.652 -0.1700 23.42 1.621 -0.1700 24.00 1.354 -0.1700 23.45 1.368 -0.1700 22.48 1.311 -0.1700 21.45 1.263 -0.1700 20.42 1.238 -0.1700 19.43 1.200 -0.1700 18.49 1.167 -0.1700 17.42 1.155 -0.1700 16.44 1.242 -0.1700 15.93 1.731 -0.1700 14.52 1.722 -0.1700 13.57 1.710 -0.1700 12.47 1.698 -0.1700 11.30 1.678 -0.1700 10.42 1.641 -0.1700 9.48 1.588 -0.1700 8.43 1.520 -0.1700 7.51 1.451 -0.1700 6.50 1.365 -0.1700 5.47 1.276 -0.1700 4.44 1.183 -0.1700 3.43 1.084 -0.1700 2.37 0.980 -0.1700 1.38 0.882 -0.1700 0.36 0.781 -0.1700 -0.70 0.674 -0.1700 -1.70 0.574 -0.1700 -2.73 0.461 -0.1700 -3.79 0.346 -0.1700 -4.78 0.241 -0.1700 -5.83 0.125 -0.1700 -6.76 -0.054 -0.1700 -7.87 -0.179 -0.1700 Tabulated from data in file JG00508.DAT & reduced using program Q01.00L Average Reynolds #: 303400 Number of angles of attack: 65 alpha / Cl / Cm -7.66 -0.125 -0.1700 -6.93 -0.033 -0.1700 -5.89 0.143 -0.1700 -4.88 0.253 -0.1700 -3.85 0.364 -0.1700 -2.80 0.480 -0.1700 -1.76 0.594 -0.1700 -0.73 0.700 -0.1700 0.30 0.804 -0.1700 1.31 0.907 -0.1700 2.34 1.012 -0.1700 3.37 1.117 -0.1700 4.42 1.219 -0.1700 5.43 1.310 -0.1700 6.46 1.391 -0.1700 7.47 1.477 -0.1700 8.50 1.548 -0.1700 9.52 1.611 -0.1700 10.50 1.662 -0.1700 11.48 1.697 -0.1700 12.52 1.713 -0.1700 13.57 1.723 -0.1700 14.58 1.739 -0.1700 15.68 1.747 -0.1700 16.74 1.747 -0.1700 17.61 1.742 -0.1700 18.65 1.748 -0.1700 19.65 1.733 -0.1700 20.52 1.728 -0.1700 21.43 1.693 -0.1700 22.45 1.678 -0.1700 22.92 1.339 -0.1700 24.42 1.353 -0.1700 23.44 1.358 -0.1700 22.47 1.320 -0.1700 21.41 1.273 -0.1700 20.46 1.240 -0.1700 19.46 1.199 -0.1700 18.44 1.170 -0.1700 17.51 1.225 -0.1700 16.93 1.741 -0.1700 15.27 1.742 -0.1700 14.31 1.734 -0.1700 13.18 1.716 -0.1700 12.32 1.707 -0.1700 11.37 1.690 -0.1700 10.48 1.656 -0.1700 9.51 1.600 -0.1700 8.50 1.534 -0.1700 7.47 1.458 -0.1700 6.49 1.379 -0.1700 5.47 1.299 -0.1700 4.45 1.207 -0.1700 3.38 1.096 -0.1700 2.39 0.997 -0.1700 1.35 0.891 -0.1700 0.33 0.785 -0.1700 -0.70 0.679 -0.1700 -1.71 0.574 -0.1700 -2.72 0.458 -0.1700 -3.75 0.343 -0.1700 -4.79 0.232 -0.1700 -5.82 0.122 -0.1700 -6.88 -0.064 -0.1700 -7.96 -0.174 -0.1700 Tabulated from data in file JG00510.DAT & reduced using program Q01.00L File fx63137b.lft created on 12-05-1997 at 15:25:49 using program FORMAT :::::::::::::: FX74MOD.LFT :::::::::::::: Airfoil: FX 74-CL5-140 MOD Builder: C. Hollinger Comment: clean Number of Reynolds #'s: 6 Average Reynolds #: 99300 Number of angles of attack: 65 alpha / Cl / Cm -5.94 0.174 -0.2500 -4.84 0.198 -0.2500 -3.86 0.244 -0.2500 -2.88 0.357 -0.2500 -1.65 0.617 -0.2500 -0.71 0.793 -0.2500 0.47 0.919 -0.2500 1.41 1.013 -0.2500 2.44 1.051 -0.2500 3.33 0.906 -0.2500 4.39 0.841 -0.2500 5.42 0.869 -0.2500 6.43 0.914 -0.2500 7.32 0.948 -0.2500 8.47 0.989 -0.2500 9.33 1.004 -0.2500 10.47 1.046 -0.2500 11.38 1.043 -0.2500 12.44 1.074 -0.2500 13.37 1.094 -0.2500 14.48 1.170 -0.2500 15.44 1.159 -0.2500 16.54 1.219 -0.2500 17.42 1.266 -0.2500 18.56 1.367 -0.2500 19.51 1.372 -0.2500 20.52 1.374 -0.2500 21.59 1.446 -0.2500 22.62 1.481 -0.2500 23.58 1.696 -0.2500 24.53 1.742 -0.2500 25.56 1.771 -0.2500 26.63 1.804 -0.2500 25.67 1.765 -0.2500 24.71 1.712 -0.2500 23.59 1.692 -0.2500 22.62 1.717 -0.2500 21.69 1.800 -0.2500 20.58 1.863 -0.2500 19.74 1.903 -0.2500 18.66 1.936 -0.2500 17.43 1.276 -0.2500 16.58 1.222 -0.2500 15.47 1.181 -0.2500 14.52 1.136 -0.2500 13.39 1.091 -0.2500 12.48 1.043 -0.2500 11.48 1.016 -0.2500 10.36 0.993 -0.2500 9.44 0.987 -0.2500 8.43 0.967 -0.2500 7.47 0.956 -0.2500 6.44 0.914 -0.2500 5.43 0.873 -0.2500 4.38 0.836 -0.2500 3.45 0.834 -0.2500 2.41 0.834 -0.2500 1.44 0.987 -0.2500 0.40 0.900 -0.2500 -0.58 0.799 -0.2500 -1.61 0.619 -0.2500 -2.68 0.375 -0.2500 -3.72 0.254 -0.2500 -4.76 0.182 -0.2500 -5.78 0.163 -0.2500 Tabulated from data in file MS00302.DAT & reduced using program Q01.00L Average Reynolds #: 124600 Number of angles of attack: 65 alpha / Cl / Cm -5.88 0.170 -0.2500 -4.89 0.193 -0.2500 -3.85 0.265 -0.2500 -2.75 0.411 -0.2500 -1.70 0.660 -0.2500 -0.59 0.845 -0.2500 0.36 0.950 -0.2500 1.60 1.068 -0.2500 2.50 1.140 -0.2500 3.30 0.819 -0.2500 4.48 0.841 -0.2500 5.39 0.861 -0.2500 6.42 0.916 -0.2500 7.47 0.930 -0.2500 8.47 0.953 -0.2500 9.51 0.986 -0.2500 10.49 1.003 -0.2500 11.53 1.030 -0.2500 12.47 1.061 -0.2500 13.46 1.088 -0.2500 14.43 1.134 -0.2500 15.46 1.196 -0.2500 16.46 1.238 -0.2500 17.56 1.261 -0.2500 18.46 1.322 -0.2500 19.68 1.377 -0.2500 20.61 1.395 -0.2500 21.66 1.472 -0.2500 22.67 1.691 -0.2500 23.53 1.680 -0.2500 24.74 1.725 -0.2500 25.70 1.729 -0.2500 26.56 1.743 -0.2500 25.59 1.706 -0.2500 24.65 1.725 -0.2500 23.69 1.705 -0.2500 22.65 1.681 -0.2500 21.69 1.737 -0.2500 20.61 1.821 -0.2500 19.71 1.861 -0.2500 18.73 1.916 -0.2500 17.64 1.933 -0.2500 16.36 1.209 -0.2500 15.56 1.192 -0.2500 14.41 1.133 -0.2500 13.38 1.091 -0.2500 12.44 1.096 -0.2500 11.47 1.022 -0.2500 10.50 1.001 -0.2500 9.49 0.966 -0.2500 8.49 0.962 -0.2500 7.44 0.915 -0.2500 6.51 0.905 -0.2500 5.47 0.873 -0.2500 4.43 0.833 -0.2500 3.48 0.815 -0.2500 2.55 1.134 -0.2500 1.41 1.034 -0.2500 0.48 0.945 -0.2500 -0.56 0.828 -0.2500 -1.64 0.659 -0.2500 -2.67 0.412 -0.2500 -3.71 0.271 -0.2500 -4.74 0.190 -0.2500 -5.80 0.166 -0.2500 Tabulated from data in file MS00304.DAT & reduced using program Q01.00L Average Reynolds #: 148000 Number of angles of attack: 65 alpha / Cl / Cm -5.88 0.162 -0.2500 -4.86 0.198 -0.2500 -3.87 0.264 -0.2500 -2.76 0.444 -0.2500 -1.74 0.666 -0.2500 -0.55 0.862 -0.2500 0.55 0.980 -0.2500 1.48 1.075 -0.2500 2.60 1.181 -0.2500 3.51 1.267 -0.2500 4.63 1.374 -0.2500 5.51 1.446 -0.2500 6.49 1.520 -0.2500 7.54 1.609 -0.2500 8.56 1.678 -0.2500 9.57 1.750 -0.2500 10.72 1.797 -0.2500 11.54 1.040 -0.2500 12.57 1.086 -0.2500 13.49 1.121 -0.2500 14.60 1.187 -0.2500 15.43 1.184 -0.2500 16.49 1.225 -0.2500 17.48 1.255 -0.2500 18.48 1.284 -0.2500 19.48 1.322 -0.2500 20.50 1.351 -0.2500 21.63 1.454 -0.2500 22.75 1.643 -0.2500 23.70 1.683 -0.2500 24.64 1.736 -0.2500 25.75 1.761 -0.2500 26.54 1.762 -0.2500 25.60 1.749 -0.2500 24.59 1.762 -0.2500 23.67 1.682 -0.2500 22.53 1.665 -0.2500 21.56 1.722 -0.2500 20.61 1.782 -0.2500 19.66 1.861 -0.2500 18.69 1.917 -0.2500 17.76 1.953 -0.2500 16.65 2.003 -0.2500 15.68 2.038 -0.2500 14.22 1.154 -0.2500 13.44 1.119 -0.2500 12.35 1.055 -0.2500 11.42 1.061 -0.2500 10.44 1.007 -0.2500 9.25 0.963 -0.2500 8.25 0.940 -0.2500 7.26 0.915 -0.2500 6.27 0.893 -0.2500 5.33 0.872 -0.2500 4.26 0.843 -0.2500 3.33 0.852 -0.2500 2.42 1.161 -0.2500 1.39 1.060 -0.2500 0.25 0.941 -0.2500 -0.67 0.834 -0.2500 -1.63 0.666 -0.2500 -2.62 0.445 -0.2500 -3.74 0.266 -0.2500 -4.73 0.190 -0.2500 -5.79 0.164 -0.2500 Tabulated from data in file MS00303.DAT & reduced using program Q01.00L Average Reynolds #: 173400 Number of angles of attack: 65 alpha / Cl / Cm -6.24 0.154 -0.2500 -4.87 0.188 -0.2500 -3.92 0.261 -0.2500 -2.84 0.412 -0.2500 -1.85 0.657 -0.2500 -0.74 0.854 -0.2500 0.29 0.977 -0.2500 1.27 1.077 -0.2500 2.29 1.180 -0.2500 3.33 1.279 -0.2500 4.39 1.382 -0.2500 5.39 1.467 -0.2500 6.38 1.549 -0.2500 7.51 1.644 -0.2500 8.55 1.722 -0.2500 9.69 1.806 -0.2500 10.71 1.874 -0.2500 11.68 1.934 -0.2500 12.72 1.996 -0.2500 13.66 2.064 -0.2500 14.77 2.064 -0.2500 15.76 2.018 -0.2500 16.66 1.983 -0.2500 17.66 1.950 -0.2500 18.50 1.897 -0.2500 19.44 1.818 -0.2500 20.53 1.774 -0.2500 21.59 1.689 -0.2500 22.56 1.669 -0.2500 23.54 1.689 -0.2500 24.58 1.724 -0.2500 25.56 1.750 -0.2500 26.53 1.755 -0.2500 25.56 1.736 -0.2500 24.55 1.745 -0.2500 23.50 1.717 -0.2500 22.53 1.665 -0.2500 21.57 1.693 -0.2500 20.60 1.764 -0.2500 19.74 1.828 -0.2500 18.73 1.878 -0.2500 17.81 1.941 -0.2500 16.70 1.990 -0.2500 15.76 2.020 -0.2500 14.67 2.072 -0.2500 13.74 2.064 -0.2500 12.71 1.989 -0.2500 11.70 1.932 -0.2500 10.72 1.872 -0.2500 9.61 1.798 -0.2500 8.51 1.711 -0.2500 7.61 1.644 -0.2500 6.48 1.548 -0.2500 5.51 1.466 -0.2500 4.52 1.380 -0.2500 3.56 1.293 -0.2500 2.52 1.190 -0.2500 1.51 1.090 -0.2500 0.47 0.983 -0.2500 -0.58 0.860 -0.2500 -1.56 0.699 -0.2500 -2.63 0.426 -0.2500 -3.69 0.258 -0.2500 -4.76 0.177 -0.2500 -5.72 0.153 -0.2500 Tabulated from data in file MS00305.DAT & reduced using program Q01.00L Average Reynolds #: 201700 Number of angles of attack: 43 alpha / Cl / Cm -5.93 0.156 -0.2500 -3.89 0.227 -0.2500 -2.49 0.439 -0.2500 -1.02 0.783 -0.2500 0.32 0.958 -0.2500 2.02 1.130 -0.2500 3.39 1.262 -0.2500 5.17 1.424 -0.2500 6.61 1.549 -0.2500 8.27 1.686 -0.2500 9.86 1.809 -0.2500 11.52 1.928 -0.2500 12.76 2.006 -0.2500 14.51 2.037 -0.2500 15.96 1.977 -0.2500 17.44 1.906 -0.2500 18.68 1.836 -0.2500 20.21 1.736 -0.2500 21.68 1.679 -0.2500 23.17 1.658 -0.2500 24.67 1.718 -0.2500 26.05 1.710 -0.2500 24.32 1.694 -0.2500 22.78 1.647 -0.2500 21.10 1.684 -0.2500 19.59 1.790 -0.2500 18.22 1.859 -0.2500 16.72 1.931 -0.2500 15.45 1.989 -0.2500 13.75 2.062 -0.2500 12.25 1.972 -0.2500 10.52 1.857 -0.2500 9.29 1.765 -0.2500 7.70 1.634 -0.2500 6.34 1.519 -0.2500 4.72 1.372 -0.2500 3.19 1.230 -0.2500 1.68 1.078 -0.2500 0.07 0.906 -0.2500 -1.38 0.679 -0.2500 -2.94 0.335 -0.2500 -4.66 0.177 -0.2500 -5.93 0.157 -0.2500 Tabulated from data in file PG00579.DAT & reduced using program Q01.00L Average Reynolds #: 302100 Number of angles of attack: 43 alpha / Cl / Cm -5.67 0.159 -0.2500 -4.12 0.240 -0.2500 -2.79 0.430 -0.2500 -1.19 0.787 -0.2500 0.38 0.995 -0.2500 1.94 1.158 -0.2500 3.47 1.314 -0.2500 4.99 1.437 -0.2500 6.51 1.561 -0.2500 8.08 1.711 -0.2500 9.60 1.837 -0.2500 11.16 1.956 -0.2500 12.67 2.048 -0.2500 14.16 2.015 -0.2500 15.60 1.966 -0.2500 17.14 1.867 -0.2500 18.40 1.796 -0.2500 20.01 1.704 -0.2500 21.52 1.654 -0.2500 23.01 1.651 -0.2500 24.52 1.731 -0.2500 26.02 1.750 -0.2500 24.54 1.715 -0.2500 23.05 1.668 -0.2500 21.46 1.637 -0.2500 20.02 1.701 -0.2500 18.63 1.778 -0.2500 17.12 1.861 -0.2500 15.51 1.958 -0.2500 14.11 2.010 -0.2500 12.49 2.031 -0.2500 11.03 1.940 -0.2500 9.55 1.824 -0.2500 7.97 1.688 -0.2500 6.44 1.538 -0.2500 4.95 1.415 -0.2500 3.41 1.283 -0.2500 1.90 1.132 -0.2500 0.34 0.964 -0.2500 -1.24 0.740 -0.2500 -2.79 0.390 -0.2500 -4.66 0.186 -0.2500 -6.01 0.156 -0.2500 Tabulated from data in file PG00578.DAT & reduced using program Q01.00L File fx74mod.lft created on 12-05-1997 at 15:25:49 using program FORMAT :::::::::::::: GEMINI.LFT :::::::::::::: Airfoil: GEMINI Builder: K. Bates Comment: clean Number of Reynolds #'s: 3 Average Reynolds #: 102200 Number of angles of attack: 33 alpha / Cl / Cm -7.07 -0.505 -0.0480 -3.42 -0.080 -0.0480 -2.77 -0.036 -0.0480 -1.16 0.087 -0.0480 0.47 0.326 -0.0480 2.04 0.484 -0.0480 3.58 0.601 -0.0480 5.09 0.730 -0.0480 6.47 0.847 -0.0480 8.33 1.005 -0.0480 9.65 1.111 -0.0480 11.09 1.201 -0.0480 12.69 1.177 -0.0480 14.07 1.153 -0.0480 15.56 1.152 -0.0480 17.15 1.120 -0.0480 18.64 0.833 -0.0480 16.74 1.114 -0.0480 15.44 1.141 -0.0480 13.77 1.152 -0.0480 12.46 1.180 -0.0480 10.91 1.188 -0.0480 9.33 1.079 -0.0480 7.77 0.950 -0.0480 6.17 0.815 -0.0480 4.50 0.672 -0.0480 3.15 0.560 -0.0480 1.64 0.451 -0.0480 0.14 0.279 -0.0480 -1.40 0.051 -0.0480 -2.98 -0.062 -0.0480 -4.43 -0.178 -0.0480 -6.13 -0.377 -0.0480 Tabulated from data in file JG00216.DAT & reduced using program Q01.00L Average Reynolds #: 204400 Number of angles of attack: 33 alpha / Cl / Cm -5.75 -0.267 -0.0480 -3.92 -0.128 -0.0480 -2.40 -0.004 -0.0480 -1.07 0.117 -0.0480 0.43 0.265 -0.0480 2.07 0.468 -0.0480 3.52 0.632 -0.0480 5.20 0.773 -0.0480 6.56 0.892 -0.0480 8.14 1.028 -0.0480 9.74 1.141 -0.0480 11.04 1.151 -0.0480 12.63 1.107 -0.0480 14.09 1.110 -0.0480 15.68 1.118 -0.0480 17.06 1.093 -0.0480 18.20 0.847 -0.0480 16.86 1.101 -0.0480 15.43 1.104 -0.0480 13.69 1.108 -0.0480 12.36 1.109 -0.0480 10.90 1.148 -0.0480 9.40 1.119 -0.0480 7.72 0.984 -0.0480 6.20 0.851 -0.0480 4.65 0.718 -0.0480 3.03 0.581 -0.0480 1.51 0.385 -0.0480 0.02 0.207 -0.0480 -1.42 0.070 -0.0480 -3.17 -0.085 -0.0480 -4.49 -0.185 -0.0480 -6.29 -0.319 -0.0480 Tabulated from data in file JG00218.DAT & reduced using program Q01.00L Average Reynolds #: 305600 Number of angles of attack: 33 alpha / Cl / Cm -5.84 -0.281 -0.0480 -4.42 -0.168 -0.0480 -2.52 -0.017 -0.0480 -1.10 0.116 -0.0480 0.73 0.301 -0.0480 2.03 0.437 -0.0480 3.41 0.603 -0.0480 5.30 0.797 -0.0480 6.72 0.922 -0.0480 8.20 1.053 -0.0480 9.65 1.121 -0.0480 11.19 1.127 -0.0480 12.54 1.120 -0.0480 14.22 1.130 -0.0480 15.72 1.139 -0.0480 17.26 1.119 -0.0480 18.13 0.938 -0.0480 16.79 1.126 -0.0480 15.35 1.143 -0.0480 13.86 1.127 -0.0480 12.42 1.117 -0.0480 10.90 1.126 -0.0480 9.35 1.111 -0.0480 7.76 1.009 -0.0480 6.13 0.864 -0.0480 4.67 0.737 -0.0480 3.01 0.546 -0.0480 1.47 0.371 -0.0480 -0.10 0.210 -0.0480 -1.64 0.054 -0.0480 -2.98 -0.065 -0.0480 -4.80 -0.207 -0.0480 -6.29 -0.326 -0.0480 Tabulated from data in file MS00220.DAT & reduced using program Q01.00L File gemini.lft created on 12-05-1997 at 15:25:49 using program FORMAT :::::::::::::: GM15.LFT :::::::::::::: Airfoil: GM15 Builder: G. Morris Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 30600 Number of angles of attack: 49 alpha / Cl / Cm -3.44 -0.043 -0.1540 -2.36 0.087 -0.1540 -1.30 0.190 -0.1540 -0.33 0.275 -0.1540 0.76 0.386 -0.1540 1.75 0.476 -0.1540 2.77 0.561 -0.1540 3.66 0.682 -0.1540 4.84 0.853 -0.1540 5.82 0.948 -0.1540 6.90 1.084 -0.1540 7.95 1.129 -0.1540 8.87 1.210 -0.1540 9.92 1.257 -0.1540 10.93 1.323 -0.1540 11.84 1.364 -0.1540 12.86 1.391 -0.1540 14.04 1.419 -0.1540 14.96 1.437 -0.1540 16.02 1.418 -0.1540 16.99 1.397 -0.1540 17.84 1.284 -0.1540 18.89 1.317 -0.1540 19.98 1.306 -0.1540 20.89 1.314 -0.1540 19.96 1.258 -0.1540 18.90 1.281 -0.1540 17.94 1.266 -0.1540 16.91 1.247 -0.1540 15.97 1.269 -0.1540 14.96 1.326 -0.1540 13.97 1.408 -0.1540 12.96 1.366 -0.1540 12.03 1.369 -0.1540 10.95 1.378 -0.1540 9.96 1.302 -0.1540 8.95 1.255 -0.1540 7.93 1.209 -0.1540 6.92 1.119 -0.1540 5.85 1.004 -0.1540 4.80 0.872 -0.1540 3.75 0.675 -0.1540 2.79 0.588 -0.1540 1.75 0.502 -0.1540 0.71 0.398 -0.1540 -0.29 0.282 -0.1540 -1.34 0.184 -0.1540 -2.41 0.070 -0.1540 -3.39 -0.023 -0.1540 Tabulated from data in file JG00403.DAT & reduced using program Q01.00L Average Reynolds #: 40200 Number of angles of attack: 49 alpha / Cl / Cm -3.55 -0.055 -0.1540 -2.44 0.079 -0.1540 -1.44 0.177 -0.1540 -0.48 0.264 -0.1540 0.71 0.371 -0.1540 1.56 0.453 -0.1540 2.65 0.578 -0.1540 3.75 0.752 -0.1540 4.67 0.880 -0.1540 5.76 0.991 -0.1540 6.88 1.087 -0.1540 7.84 1.155 -0.1540 8.84 1.231 -0.1540 9.90 1.290 -0.1540 10.87 1.270 -0.1540 11.82 1.275 -0.1540 12.87 1.311 -0.1540 13.83 1.317 -0.1540 14.88 1.323 -0.1540 16.00 1.322 -0.1540 16.94 1.221 -0.1540 17.88 1.160 -0.1540 18.99 1.171 -0.1540 19.87 1.242 -0.1540 20.81 1.232 -0.1540 19.90 1.178 -0.1540 18.92 1.201 -0.1540 17.90 1.183 -0.1540 16.95 1.302 -0.1540 16.00 1.349 -0.1540 14.94 1.303 -0.1540 14.05 1.315 -0.1540 12.98 1.302 -0.1540 12.02 1.306 -0.1540 10.92 1.276 -0.1540 9.94 1.270 -0.1540 8.91 1.222 -0.1540 7.93 1.165 -0.1540 6.82 1.076 -0.1540 5.87 1.010 -0.1540 4.83 0.903 -0.1540 3.84 0.759 -0.1540 2.74 0.600 -0.1540 1.75 0.488 -0.1540 0.71 0.371 -0.1540 -0.26 0.278 -0.1540 -1.36 0.179 -0.1540 -2.40 0.078 -0.1540 -3.43 -0.041 -0.1540 Tabulated from data in file JG00402.DAT & reduced using program Q01.00L Average Reynolds #: 60900 Number of angles of attack: 33 alpha / Cl / Cm -3.53 0.000 -0.1540 -1.94 0.173 -0.1540 -0.41 0.317 -0.1540 1.12 0.482 -0.1540 2.69 0.727 -0.1540 4.25 0.911 -0.1540 5.78 1.042 -0.1540 7.30 1.170 -0.1540 8.92 1.251 -0.1540 10.34 1.304 -0.1540 11.93 1.339 -0.1540 13.32 1.324 -0.1540 14.93 1.286 -0.1540 16.31 1.282 -0.1540 17.87 1.179 -0.1540 19.27 1.166 -0.1540 20.88 1.224 -0.1540 19.35 1.166 -0.1540 17.86 1.196 -0.1540 16.38 1.270 -0.1540 14.87 1.300 -0.1540 13.38 1.317 -0.1540 11.94 1.326 -0.1540 10.38 1.292 -0.1540 8.92 1.234 -0.1540 7.40 1.163 -0.1540 5.84 1.027 -0.1540 4.27 0.891 -0.1540 2.71 0.698 -0.1540 1.16 0.463 -0.1540 -0.39 0.299 -0.1540 -1.91 0.159 -0.1540 -3.51 -0.006 -0.1540 Tabulated from data in file JG00400.DAT & reduced using program Q01.00L Average Reynolds #: 101200 Number of angles of attack: 33 alpha / Cl / Cm -3.39 0.025 -0.1540 -1.43 0.240 -0.1540 0.01 0.419 -0.1540 1.55 0.635 -0.1540 3.10 0.812 -0.1540 4.59 0.946 -0.1540 6.12 1.077 -0.1540 7.52 1.180 -0.1540 9.08 1.244 -0.1540 10.55 1.301 -0.1540 12.41 1.326 -0.1540 13.94 1.261 -0.1540 15.35 1.240 -0.1540 16.84 1.216 -0.1540 18.29 1.121 -0.1540 19.84 1.135 -0.1540 21.36 1.189 -0.1540 18.15 1.112 -0.1540 17.61 1.143 -0.1540 15.98 1.224 -0.1540 14.63 1.264 -0.1540 13.13 1.334 -0.1540 11.55 1.313 -0.1540 10.17 1.279 -0.1540 8.46 1.206 -0.1540 6.94 1.130 -0.1540 5.63 1.021 -0.1540 4.17 0.886 -0.1540 2.20 0.695 -0.1540 0.91 0.521 -0.1540 -0.77 0.289 -0.1540 -2.15 0.141 -0.1540 -3.94 -0.097 -0.1540 Tabulated from data in file MS00394.DAT & reduced using program Q01.00L Average Reynolds #: 201800 Number of angles of attack: 33 alpha / Cl / Cm -3.34 0.133 -0.1540 -1.65 0.339 -0.1540 -0.33 0.503 -0.1540 1.47 0.676 -0.1540 2.96 0.822 -0.1540 4.66 0.987 -0.1540 5.94 1.098 -0.1540 7.58 1.196 -0.1540 9.02 1.268 -0.1540 10.67 1.317 -0.1540 12.14 1.373 -0.1540 13.58 1.343 -0.1540 14.85 1.333 -0.1540 16.31 1.304 -0.1540 17.85 1.101 -0.1540 19.31 1.135 -0.1540 20.83 1.176 -0.1540 19.17 1.133 -0.1540 17.55 1.099 -0.1540 16.12 1.283 -0.1540 14.59 1.298 -0.1540 13.24 1.360 -0.1540 11.76 1.362 -0.1540 10.22 1.304 -0.1540 8.71 1.251 -0.1540 6.97 1.162 -0.1540 5.50 1.056 -0.1540 3.89 0.904 -0.1540 2.34 0.751 -0.1540 0.64 0.587 -0.1540 -0.65 0.454 -0.1540 -2.25 0.249 -0.1540 -3.71 0.068 -0.1540 Tabulated from data in file JG00398.DAT & reduced using program Q01.00L File gm15.lft created on 12-05-1997 at 15:25:49 using program FORMAT :::::::::::::: GM15F1.LFT :::::::::::::: Airfoil: GM15 Builder: G. Morris Comment: reflexed (flap = -8.5 degs) Number of Reynolds #'s: 4 Average Reynolds #: 61100 Number of angles of attack: 49 alpha / Cl / Cm -3.50 -0.492 -0.1140 -2.39 -0.377 -0.1140 -1.34 -0.246 -0.1140 -0.50 -0.171 -0.1140 0.66 -0.068 -0.1140 1.64 0.031 -0.1140 2.62 0.132 -0.1140 3.61 0.259 -0.1140 4.64 0.377 -0.1140 5.67 0.480 -0.1140 6.67 0.571 -0.1140 7.70 0.667 -0.1140 8.73 0.763 -0.1140 9.74 0.854 -0.1140 10.80 0.945 -0.1140 11.74 1.013 -0.1140 12.81 1.076 -0.1140 13.87 1.128 -0.1140 14.78 1.147 -0.1140 15.81 1.144 -0.1140 16.77 1.177 -0.1140 17.77 1.111 -0.1140 18.81 1.109 -0.1140 19.86 1.101 -0.1140 20.73 1.077 -0.1140 19.88 1.119 -0.1140 19.01 1.102 -0.1140 17.94 1.129 -0.1140 16.93 1.136 -0.1140 15.94 1.176 -0.1140 14.91 1.156 -0.1140 13.93 1.137 -0.1140 12.93 1.084 -0.1140 11.87 1.016 -0.1140 10.91 0.948 -0.1140 9.85 0.857 -0.1140 8.82 0.761 -0.1140 7.84 0.668 -0.1140 6.74 0.568 -0.1140 5.75 0.477 -0.1140 4.76 0.382 -0.1140 3.73 0.270 -0.1140 2.66 0.126 -0.1140 1.61 0.018 -0.1140 0.64 -0.074 -0.1140 -0.47 -0.182 -0.1140 -1.45 -0.275 -0.1140 -2.60 -0.409 -0.1140 -3.56 -0.500 -0.1140 Tabulated from data in file MS00410.DAT & reduced using program Q01.00L Average Reynolds #: 101800 Number of angles of attack: 33 alpha / Cl / Cm -3.44 -0.514 -0.1140 -1.85 -0.310 -0.1140 -0.18 -0.144 -0.1140 1.29 -0.013 -0.1140 2.65 0.139 -0.1140 4.14 0.286 -0.1140 5.66 0.439 -0.1140 7.31 0.599 -0.1140 8.69 0.733 -0.1140 10.38 0.885 -0.1140 11.80 0.985 -0.1140 13.38 1.077 -0.1140 14.73 1.086 -0.1140 16.35 1.008 -0.1140 17.84 1.003 -0.1140 19.39 0.973 -0.1140 20.76 0.957 -0.1140 19.28 0.984 -0.1140 17.74 1.012 -0.1140 16.28 1.054 -0.1140 14.85 1.119 -0.1140 13.38 1.069 -0.1140 11.83 0.976 -0.1140 10.28 0.864 -0.1140 8.76 0.724 -0.1140 7.23 0.574 -0.1140 5.73 0.427 -0.1140 4.10 0.261 -0.1140 2.59 0.115 -0.1140 1.05 -0.057 -0.1140 -0.63 -0.210 -0.1140 -2.07 -0.367 -0.1140 -3.60 -0.532 -0.1140 Tabulated from data in file JG00406.DAT & reduced using program Q01.00L Average Reynolds #: 203500 Number of angles of attack: 33 alpha / Cl / Cm -3.42 -0.524 -0.1140 -1.82 -0.278 -0.1140 0.02 -0.088 -0.1140 1.54 0.016 -0.1140 3.04 0.163 -0.1140 4.49 0.302 -0.1140 5.96 0.485 -0.1140 7.50 0.645 -0.1140 9.14 0.806 -0.1140 10.61 0.927 -0.1140 12.02 1.030 -0.1140 13.58 1.107 -0.1140 14.73 1.145 -0.1140 16.48 1.151 -0.1140 17.88 1.127 -0.1140 19.66 1.021 -0.1140 20.91 0.980 -0.1140 19.07 1.066 -0.1140 17.46 1.128 -0.1140 16.21 1.152 -0.1140 14.94 1.144 -0.1140 13.23 1.089 -0.1140 11.72 1.007 -0.1140 10.20 0.892 -0.1140 8.65 0.754 -0.1140 7.12 0.597 -0.1140 5.41 0.412 -0.1140 4.00 0.241 -0.1140 2.38 0.084 -0.1140 0.77 -0.059 -0.1140 -0.74 -0.172 -0.1140 -2.40 -0.389 -0.1140 -3.64 -0.557 -0.1140 Tabulated from data in file MS00411.DAT & reduced using program Q01.00L Average Reynolds #: 304300 Number of angles of attack: 33 alpha / Cl / Cm -3.44 -0.517 -0.1140 -1.86 -0.275 -0.1140 -0.32 -0.121 -0.1140 1.95 0.049 -0.1140 2.95 0.157 -0.1140 4.57 0.344 -0.1140 5.99 0.493 -0.1140 7.60 0.658 -0.1140 9.06 0.799 -0.1140 10.57 0.927 -0.1140 12.08 1.042 -0.1140 13.66 1.128 -0.1140 14.52 1.148 -0.1140 16.02 1.161 -0.1140 17.71 1.118 -0.1140 19.24 1.003 -0.1140 20.37 1.034 -0.1140 19.10 0.975 -0.1140 17.79 1.123 -0.1140 16.55 1.168 -0.1140 15.21 1.156 -0.1140 13.21 1.100 -0.1140 11.72 1.011 -0.1140 10.12 0.885 -0.1140 8.45 0.737 -0.1140 7.00 0.589 -0.1140 5.39 0.419 -0.1140 3.94 0.269 -0.1140 2.32 0.078 -0.1140 0.06 -0.095 -0.1140 -0.81 -0.178 -0.1140 -2.29 -0.354 -0.1140 -3.61 -0.549 -0.1140 Tabulated from data in file MS00413.DAT & reduced using program Q01.00L File gm15f1.lft created on 12-05-1997 at 15:25:49 using program FORMAT :::::::::::::: J5012.LFT :::::::::::::: Airfoil: J5012 Builder: J. Raskin Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 40700 Number of angles of attack: 97 alpha / Cl / Cm -6.28 -0.563 0.0000 -5.68 -0.529 0.0000 -5.01 -0.481 0.0000 -4.57 -0.446 0.0000 -3.94 -0.386 0.0000 -3.61 -0.346 0.0000 -2.96 -0.243 0.0000 -2.51 -0.162 0.0000 -1.88 -0.069 0.0000 -1.44 -0.034 0.0000 -0.80 -0.001 0.0000 -0.47 0.014 0.0000 0.11 0.045 0.0000 0.53 0.059 0.0000 1.19 0.083 0.0000 1.57 0.109 0.0000 2.13 0.172 0.0000 2.56 0.236 0.0000 3.24 0.340 0.0000 3.61 0.400 0.0000 4.26 0.507 0.0000 4.65 0.553 0.0000 5.27 0.605 0.0000 5.70 0.636 0.0000 6.18 0.664 0.0000 6.71 0.690 0.0000 7.26 0.721 0.0000 7.76 0.742 0.0000 8.32 0.764 0.0000 8.73 0.783 0.0000 9.32 0.813 0.0000 9.77 0.829 0.0000 10.26 0.840 0.0000 10.80 0.806 0.0000 11.31 0.823 0.0000 11.74 0.798 0.0000 12.26 0.778 0.0000 12.76 0.732 0.0000 13.16 0.725 0.0000 13.73 0.718 0.0000 14.11 0.689 0.0000 14.75 0.710 0.0000 15.21 0.691 0.0000 15.73 0.694 0.0000 16.33 0.687 0.0000 16.66 0.695 0.0000 17.18 0.712 0.0000 17.75 0.778 0.0000 18.30 0.800 0.0000 17.75 0.723 0.0000 17.29 0.721 0.0000 16.81 0.702 0.0000 16.29 0.724 0.0000 15.83 0.674 0.0000 15.24 0.673 0.0000 14.85 0.682 0.0000 14.29 0.701 0.0000 13.89 0.742 0.0000 13.27 0.712 0.0000 12.90 0.769 0.0000 12.37 0.842 0.0000 11.86 0.838 0.0000 11.32 0.834 0.0000 10.91 0.852 0.0000 10.33 0.839 0.0000 9.89 0.834 0.0000 9.44 0.795 0.0000 8.90 0.782 0.0000 8.45 0.763 0.0000 7.88 0.742 0.0000 7.25 0.714 0.0000 6.75 0.685 0.0000 6.28 0.653 0.0000 5.76 0.621 0.0000 5.28 0.585 0.0000 4.73 0.538 0.0000 4.20 0.476 0.0000 3.82 0.420 0.0000 3.35 0.329 0.0000 2.73 0.240 0.0000 2.25 0.172 0.0000 1.61 0.104 0.0000 1.24 0.070 0.0000 0.58 0.037 0.0000 0.16 0.020 0.0000 -0.43 -0.013 0.0000 -0.88 -0.026 0.0000 -1.41 -0.041 0.0000 -1.77 -0.065 0.0000 -2.45 -0.141 0.0000 -2.94 -0.242 0.0000 -3.53 -0.327 0.0000 -3.85 -0.365 0.0000 -4.48 -0.428 0.0000 -4.87 -0.460 0.0000 -5.43 -0.513 0.0000 -5.94 -0.543 0.0000 Tabulated from data in file MS00290.DAT & reduced using program Q01.00L Average Reynolds #: 61000 Number of angles of attack: 97 alpha / Cl / Cm -6.28 -0.558 0.0000 -5.67 -0.519 0.0000 -4.99 -0.478 0.0000 -4.64 -0.451 0.0000 -4.01 -0.401 0.0000 -3.56 -0.371 0.0000 -3.02 -0.335 0.0000 -2.58 -0.299 0.0000 -2.02 -0.199 0.0000 -1.47 -0.082 0.0000 -0.93 -0.004 0.0000 -0.43 0.017 0.0000 0.04 0.030 0.0000 0.55 0.048 0.0000 1.08 0.066 0.0000 1.58 0.152 0.0000 2.15 0.252 0.0000 2.54 0.331 0.0000 3.14 0.423 0.0000 3.66 0.471 0.0000 4.25 0.515 0.0000 4.66 0.539 0.0000 5.18 0.575 0.0000 5.69 0.617 0.0000 6.22 0.653 0.0000 6.75 0.687 0.0000 7.23 0.716 0.0000 7.80 0.745 0.0000 8.25 0.774 0.0000 8.84 0.809 0.0000 9.25 0.829 0.0000 9.83 0.851 0.0000 10.19 0.861 0.0000 10.75 0.871 0.0000 11.13 0.864 0.0000 11.83 0.856 0.0000 12.24 0.834 0.0000 12.78 0.831 0.0000 13.21 0.794 0.0000 13.77 0.769 0.0000 14.21 0.766 0.0000 14.79 0.774 0.0000 15.32 0.771 0.0000 15.76 0.771 0.0000 16.23 0.799 0.0000 16.79 0.776 0.0000 17.21 0.786 0.0000 17.75 0.773 0.0000 18.20 0.791 0.0000 17.87 0.774 0.0000 17.47 0.768 0.0000 16.87 0.761 0.0000 16.44 0.781 0.0000 15.87 0.770 0.0000 15.42 0.768 0.0000 14.86 0.810 0.0000 14.41 0.767 0.0000 13.83 0.758 0.0000 13.47 0.798 0.0000 12.88 0.826 0.0000 12.48 0.804 0.0000 11.86 0.822 0.0000 11.42 0.842 0.0000 10.86 0.851 0.0000 10.52 0.840 0.0000 9.85 0.822 0.0000 9.51 0.812 0.0000 8.84 0.778 0.0000 8.46 0.755 0.0000 7.82 0.717 0.0000 7.43 0.694 0.0000 6.85 0.654 0.0000 6.38 0.629 0.0000 5.86 0.594 0.0000 5.36 0.558 0.0000 4.81 0.515 0.0000 4.33 0.479 0.0000 3.77 0.441 0.0000 3.36 0.412 0.0000 2.78 0.344 0.0000 2.27 0.244 0.0000 1.70 0.139 0.0000 1.19 0.049 0.0000 0.70 0.002 0.0000 0.21 -0.017 0.0000 -0.34 -0.017 0.0000 -0.83 -0.033 0.0000 -1.36 -0.102 0.0000 -1.84 -0.201 0.0000 -2.39 -0.318 0.0000 -2.86 -0.369 0.0000 -3.39 -0.402 0.0000 -3.88 -0.424 0.0000 -4.42 -0.455 0.0000 -4.97 -0.506 0.0000 -5.41 -0.541 0.0000 -5.98 -0.577 0.0000 Tabulated from data in file MS00291.DAT & reduced using program Q01.00L Average Reynolds #: 81900 Number of angles of attack: 97 alpha / Cl / Cm -5.96 -0.549 0.0000 -5.63 -0.529 0.0000 -5.03 -0.490 0.0000 -4.56 -0.451 0.0000 -3.93 -0.383 0.0000 -3.61 -0.364 0.0000 -3.01 -0.352 0.0000 -2.59 -0.330 0.0000 -1.87 -0.271 0.0000 -1.53 -0.234 0.0000 -0.92 -0.119 0.0000 -0.50 -0.043 0.0000 0.16 0.027 0.0000 0.54 0.048 0.0000 1.20 0.169 0.0000 1.58 0.234 0.0000 2.25 0.339 0.0000 2.64 0.381 0.0000 3.18 0.409 0.0000 3.64 0.435 0.0000 4.27 0.485 0.0000 4.63 0.530 0.0000 5.18 0.572 0.0000 5.70 0.605 0.0000 6.28 0.644 0.0000 6.73 0.674 0.0000 7.26 0.706 0.0000 7.72 0.734 0.0000 8.20 0.764 0.0000 8.80 0.801 0.0000 9.27 0.825 0.0000 9.77 0.847 0.0000 10.17 0.864 0.0000 10.76 0.868 0.0000 11.29 0.850 0.0000 11.74 0.821 0.0000 12.23 0.816 0.0000 12.77 0.829 0.0000 13.28 0.784 0.0000 13.73 0.796 0.0000 14.25 0.761 0.0000 14.76 0.783 0.0000 15.27 0.776 0.0000 15.68 0.750 0.0000 16.29 0.772 0.0000 16.69 0.754 0.0000 17.17 0.742 0.0000 17.75 0.766 0.0000 18.24 0.767 0.0000 17.77 0.751 0.0000 17.22 0.756 0.0000 16.80 0.749 0.0000 16.31 0.735 0.0000 15.91 0.770 0.0000 15.38 0.748 0.0000 14.88 0.746 0.0000 14.25 0.793 0.0000 13.82 0.769 0.0000 13.28 0.782 0.0000 12.79 0.785 0.0000 12.35 0.833 0.0000 11.91 0.808 0.0000 11.47 0.842 0.0000 10.90 0.863 0.0000 10.38 0.862 0.0000 9.93 0.840 0.0000 9.42 0.821 0.0000 8.91 0.793 0.0000 8.47 0.769 0.0000 7.86 0.729 0.0000 7.32 0.696 0.0000 6.88 0.667 0.0000 6.30 0.630 0.0000 5.82 0.601 0.0000 5.42 0.573 0.0000 4.80 0.530 0.0000 4.22 0.469 0.0000 3.69 0.424 0.0000 3.23 0.395 0.0000 2.77 0.375 0.0000 2.32 0.324 0.0000 1.76 0.247 0.0000 1.26 0.174 0.0000 0.68 0.055 0.0000 0.06 0.004 0.0000 -0.43 -0.050 0.0000 -0.87 -0.126 0.0000 -1.45 -0.245 0.0000 -1.91 -0.289 0.0000 -2.39 -0.321 0.0000 -2.83 -0.343 0.0000 -3.43 -0.376 0.0000 -3.85 -0.394 0.0000 -4.43 -0.453 0.0000 -4.90 -0.502 0.0000 -5.53 -0.542 0.0000 -5.89 -0.563 0.0000 Tabulated from data in file MS00292.DAT & reduced using program Q01.00L Average Reynolds #: 100300 Number of angles of attack: 97 alpha / Cl / Cm -5.92 -0.552 0.0000 -5.66 -0.537 0.0000 -5.05 -0.494 0.0000 -4.65 -0.468 0.0000 -4.09 -0.429 0.0000 -3.64 -0.393 0.0000 -3.01 -0.341 0.0000 -2.58 -0.315 0.0000 -2.05 -0.288 0.0000 -1.59 -0.240 0.0000 -0.97 -0.150 0.0000 -0.54 -0.071 0.0000 0.14 0.039 0.0000 0.52 0.102 0.0000 1.10 0.207 0.0000 1.56 0.281 0.0000 2.22 0.359 0.0000 2.59 0.390 0.0000 3.16 0.430 0.0000 3.61 0.463 0.0000 4.22 0.507 0.0000 4.64 0.535 0.0000 5.15 0.576 0.0000 5.65 0.612 0.0000 6.23 0.651 0.0000 6.67 0.680 0.0000 7.24 0.713 0.0000 7.77 0.749 0.0000 8.15 0.775 0.0000 8.74 0.812 0.0000 9.23 0.837 0.0000 9.68 0.858 0.0000 10.17 0.878 0.0000 10.76 0.886 0.0000 11.22 0.864 0.0000 11.76 0.844 0.0000 12.24 0.826 0.0000 12.72 0.771 0.0000 13.20 0.751 0.0000 13.72 0.762 0.0000 14.20 0.746 0.0000 14.72 0.768 0.0000 15.32 0.755 0.0000 15.65 0.748 0.0000 16.28 0.753 0.0000 16.64 0.741 0.0000 17.30 0.774 0.0000 17.70 0.741 0.0000 18.35 0.789 0.0000 17.82 0.761 0.0000 17.34 0.758 0.0000 16.90 0.756 0.0000 16.29 0.743 0.0000 15.87 0.736 0.0000 15.26 0.746 0.0000 14.83 0.752 0.0000 14.29 0.775 0.0000 13.88 0.758 0.0000 13.38 0.753 0.0000 12.87 0.805 0.0000 12.41 0.796 0.0000 11.81 0.821 0.0000 11.42 0.851 0.0000 10.85 0.872 0.0000 10.38 0.876 0.0000 9.85 0.848 0.0000 9.37 0.828 0.0000 8.86 0.802 0.0000 8.40 0.774 0.0000 7.80 0.735 0.0000 7.41 0.708 0.0000 6.78 0.668 0.0000 6.34 0.639 0.0000 5.80 0.603 0.0000 5.35 0.572 0.0000 4.75 0.527 0.0000 4.37 0.495 0.0000 3.74 0.452 0.0000 3.29 0.417 0.0000 2.72 0.379 0.0000 2.24 0.336 0.0000 1.70 0.281 0.0000 1.27 0.216 0.0000 0.69 0.123 0.0000 0.15 0.031 0.0000 -0.38 -0.051 0.0000 -0.91 -0.151 0.0000 -1.43 -0.218 0.0000 -1.85 -0.264 0.0000 -2.46 -0.304 0.0000 -2.89 -0.329 0.0000 -3.45 -0.366 0.0000 -3.96 -0.411 0.0000 -4.50 -0.454 0.0000 -4.89 -0.480 0.0000 -5.46 -0.514 0.0000 -6.01 -0.551 0.0000 Tabulated from data in file MS00293.DAT & reduced using program Q01.00L File j5012.lft created on 12-05-1997 at 15:25:50 using program FORMAT :::::::::::::: K3311.LFT :::::::::::::: Airfoil: K3311 Builder: L. Kincaid Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 61300 Number of angles of attack: 33 alpha / Cl / Cm -5.73 -0.372 -0.0850 -4.26 -0.292 -0.0850 -2.71 -0.130 -0.0850 -1.23 0.043 -0.0850 0.57 0.265 -0.0850 1.89 0.436 -0.0850 3.68 0.586 -0.0850 5.06 0.691 -0.0850 6.77 0.845 -0.0850 8.26 1.029 -0.0850 9.89 1.157 -0.0850 11.20 1.188 -0.0850 12.67 1.197 -0.0850 14.31 1.191 -0.0850 15.76 1.143 -0.0850 17.19 1.077 -0.0850 18.75 1.013 -0.0850 17.13 1.127 -0.0850 15.68 1.160 -0.0850 14.04 1.197 -0.0850 12.55 1.201 -0.0850 11.05 1.197 -0.0850 9.59 1.141 -0.0850 8.11 1.013 -0.0850 6.59 0.851 -0.0850 4.99 0.708 -0.0850 3.33 0.570 -0.0850 1.84 0.425 -0.0850 0.46 0.255 -0.0850 -1.22 0.030 -0.0850 -2.76 -0.142 -0.0850 -4.28 -0.300 -0.0850 -5.90 -0.401 -0.0850 Tabulated from data in file JG00125.DAT & reduced using program Q01.00L Average Reynolds #: 101700 Number of angles of attack: 33 alpha / Cl / Cm -5.72 -0.350 -0.0850 -4.15 -0.163 -0.0850 -2.64 0.037 -0.0850 -1.20 0.184 -0.0850 0.44 0.361 -0.0850 2.08 0.514 -0.0850 3.56 0.663 -0.0850 5.19 0.820 -0.0850 6.81 0.975 -0.0850 8.21 1.098 -0.0850 9.77 1.202 -0.0850 11.19 1.207 -0.0850 12.66 1.207 -0.0850 14.24 1.188 -0.0850 15.63 1.164 -0.0850 17.08 1.046 -0.0850 18.74 0.966 -0.0850 17.11 1.027 -0.0850 15.59 1.126 -0.0850 14.12 1.203 -0.0850 12.66 1.201 -0.0850 11.07 1.209 -0.0850 9.51 1.204 -0.0850 8.06 1.088 -0.0850 6.47 0.951 -0.0850 4.91 0.812 -0.0850 3.51 0.659 -0.0850 1.93 0.500 -0.0850 0.23 0.338 -0.0850 -1.22 0.168 -0.0850 -2.73 0.016 -0.0850 -4.29 -0.188 -0.0850 -5.96 -0.376 -0.0850 Tabulated from data in file AB00123.DAT & reduced using program Q01.00L Average Reynolds #: 203300 Number of angles of attack: 33 alpha / Cl / Cm -5.80 -0.296 -0.0850 -4.16 -0.101 -0.0850 -2.54 0.043 -0.0850 -1.05 0.175 -0.0850 0.47 0.345 -0.0850 2.14 0.525 -0.0850 3.56 0.681 -0.0850 5.17 0.848 -0.0850 6.64 0.993 -0.0850 8.17 1.130 -0.0850 9.84 1.198 -0.0850 11.16 1.201 -0.0850 12.82 1.203 -0.0850 14.29 1.193 -0.0850 15.67 1.171 -0.0850 17.19 1.031 -0.0850 18.78 1.017 -0.0850 16.88 1.056 -0.0850 15.56 1.174 -0.0850 14.12 1.196 -0.0850 12.66 1.203 -0.0850 11.01 1.203 -0.0850 9.67 1.196 -0.0850 7.87 1.104 -0.0850 6.58 0.987 -0.0850 4.72 0.799 -0.0850 3.19 0.637 -0.0850 1.66 0.470 -0.0850 0.02 0.286 -0.0850 -1.46 0.134 -0.0850 -2.79 0.015 -0.0850 -4.51 -0.143 -0.0850 -5.91 -0.313 -0.0850 Tabulated from data in file AB00121.DAT & reduced using program Q01.00L Average Reynolds #: 304600 Number of angles of attack: 33 alpha / Cl / Cm -5.69 -0.238 -0.0850 -4.31 -0.114 -0.0850 -2.76 0.027 -0.0850 -1.02 0.187 -0.0850 0.47 0.352 -0.0850 2.06 0.521 -0.0850 3.52 0.671 -0.0850 5.16 0.836 -0.0850 6.77 0.992 -0.0850 8.18 1.105 -0.0850 10.02 1.172 -0.0850 11.41 1.182 -0.0850 12.92 1.188 -0.0850 14.38 1.179 -0.0850 15.86 1.146 -0.0850 16.88 1.092 -0.0850 18.45 1.003 -0.0850 17.03 1.067 -0.0850 15.43 1.166 -0.0850 13.95 1.183 -0.0850 12.60 1.186 -0.0850 11.12 1.179 -0.0850 9.52 1.159 -0.0850 7.90 1.080 -0.0850 6.36 0.947 -0.0850 4.55 0.767 -0.0850 3.32 0.641 -0.0850 1.71 0.474 -0.0850 0.39 0.329 -0.0850 -1.47 0.134 -0.0850 -2.80 0.010 -0.0850 -4.35 -0.127 -0.0850 -5.81 -0.264 -0.0850 Tabulated from data in file AB00119.DAT & reduced using program Q01.00L File k3311.lft created on 12-05-1997 at 15:25:50 using program FORMAT :::::::::::::: M06B.LFT :::::::::::::: Airfoil: M06-13-128 (B) Builder: M. Allen Comment: clean Number of Reynolds #'s: 6 Average Reynolds #: 61400 Number of angles of attack: 57 alpha / Cl / Cm -6.01 -0.189 0.0040 -5.19 -0.103 0.0040 -4.16 -0.003 0.0040 -3.18 0.062 0.0040 -2.13 0.109 0.0040 -1.15 0.154 0.0040 -0.13 0.206 0.0040 0.91 0.240 0.0040 1.89 0.287 0.0040 2.92 0.349 0.0040 3.90 0.390 0.0040 4.92 0.433 0.0040 5.94 0.464 0.0040 6.97 0.471 0.0040 7.96 0.511 0.0040 8.95 0.528 0.0040 10.01 0.565 0.0040 10.98 0.612 0.0040 12.00 0.628 0.0040 13.03 0.664 0.0040 14.00 0.686 0.0040 15.00 0.723 0.0040 16.04 0.773 0.0040 17.01 0.820 0.0040 18.03 0.899 0.0040 19.08 1.037 0.0040 20.21 1.301 0.0040 21.14 1.197 0.0040 22.16 1.205 0.0040 21.66 1.130 0.0040 20.66 1.182 0.0040 19.61 1.206 0.0040 18.69 1.222 0.0040 17.69 1.280 0.0040 16.69 1.346 0.0040 15.71 1.387 0.0040 14.55 0.689 0.0040 13.51 0.657 0.0040 12.51 0.621 0.0040 11.49 0.586 0.0040 10.48 0.554 0.0040 9.51 0.518 0.0040 8.48 0.491 0.0040 7.46 0.456 0.0040 6.55 0.460 0.0040 5.49 0.423 0.0040 4.49 0.391 0.0040 3.44 0.328 0.0040 2.46 0.285 0.0040 1.42 0.235 0.0040 0.41 0.184 0.0040 -0.59 0.145 0.0040 -1.60 0.097 0.0040 -2.60 0.043 0.0040 -3.65 -0.014 0.0040 -4.62 -0.099 0.0040 -5.68 -0.199 0.0040 Tabulated from data in file JG00192.DAT & reduced using program Q01.00L Average Reynolds #: 71600 Number of angles of attack: 57 alpha / Cl / Cm -5.95 -0.196 0.0040 -4.86 -0.083 0.0040 -3.85 0.002 0.0040 -2.76 0.064 0.0040 -1.85 0.111 0.0040 -0.70 0.162 0.0040 0.22 0.216 0.0040 1.33 0.259 0.0040 2.35 0.313 0.0040 3.20 0.360 0.0040 4.33 0.414 0.0040 5.18 0.447 0.0040 6.34 0.509 0.0040 7.30 0.544 0.0040 8.28 0.562 0.0040 9.24 0.550 0.0040 10.39 0.596 0.0040 11.33 0.632 0.0040 12.30 0.661 0.0040 13.46 0.710 0.0040 14.38 0.724 0.0040 15.32 0.780 0.0040 16.33 0.823 0.0040 17.31 0.878 0.0040 18.44 1.287 0.0040 19.42 1.229 0.0040 20.54 1.221 0.0040 21.36 1.152 0.0040 22.44 1.153 0.0040 21.33 1.176 0.0040 20.34 1.224 0.0040 19.42 1.229 0.0040 18.37 1.269 0.0040 17.41 1.324 0.0040 16.40 1.400 0.0040 15.40 1.451 0.0040 14.41 1.499 0.0040 13.22 0.648 0.0040 12.23 0.623 0.0040 11.18 0.603 0.0040 10.21 0.576 0.0040 9.23 0.528 0.0040 8.20 0.490 0.0040 7.21 0.471 0.0040 6.13 0.462 0.0040 5.14 0.421 0.0040 4.13 0.381 0.0040 3.07 0.331 0.0040 2.06 0.268 0.0040 1.01 0.215 0.0040 0.03 0.167 0.0040 -0.90 0.128 0.0040 -1.97 0.063 0.0040 -2.98 0.010 0.0040 -3.97 -0.047 0.0040 -4.97 -0.139 0.0040 -6.12 -0.257 0.0040 Tabulated from data in file JG00193.DAT & reduced using program Q01.00L Average Reynolds #: 102000 Number of angles of attack: 57 alpha / Cl / Cm -6.04 -0.275 0.0040 -4.92 -0.143 0.0040 -3.84 -0.030 0.0040 -2.73 0.055 0.0040 -1.77 0.116 0.0040 -0.73 0.161 0.0040 0.23 0.220 0.0040 1.19 0.254 0.0040 2.39 0.322 0.0040 3.31 0.367 0.0040 4.22 0.412 0.0040 5.43 0.464 0.0040 6.39 0.511 0.0040 7.39 0.561 0.0040 8.34 0.624 0.0040 9.31 0.666 0.0040 10.34 0.727 0.0040 11.31 0.786 0.0040 12.36 0.829 0.0040 13.36 0.849 0.0040 14.36 0.850 0.0040 15.52 0.837 0.0040 16.55 0.860 0.0040 17.62 1.175 0.0040 18.59 1.218 0.0040 19.60 1.209 0.0040 20.46 1.204 0.0040 21.53 1.206 0.0040 22.46 1.099 0.0040 21.27 1.217 0.0040 20.39 1.217 0.0040 19.32 1.234 0.0040 18.36 1.237 0.0040 17.31 1.294 0.0040 16.39 1.388 0.0040 15.38 1.434 0.0040 14.46 1.492 0.0040 13.43 1.510 0.0040 12.43 1.435 0.0040 11.25 0.782 0.0040 10.22 0.732 0.0040 9.24 0.660 0.0040 8.20 0.595 0.0040 7.14 0.542 0.0040 6.08 0.479 0.0040 5.13 0.436 0.0040 4.10 0.383 0.0040 3.12 0.341 0.0040 2.01 0.281 0.0040 1.00 0.222 0.0040 0.04 0.186 0.0040 -0.99 0.131 0.0040 -2.04 0.072 0.0040 -3.04 0.001 0.0040 -4.01 -0.071 0.0040 -5.09 -0.187 0.0040 -6.03 -0.288 0.0040 Tabulated from data in file JG00194.DAT & reduced using program Q01.00L Average Reynolds #: 152700 Number of angles of attack: 57 alpha / Cl / Cm -6.03 -0.308 0.0040 -4.73 -0.151 0.0040 -3.76 -0.034 0.0040 -2.63 0.065 0.0040 -1.71 0.134 0.0040 -0.79 0.185 0.0040 0.44 0.242 0.0040 1.26 0.292 0.0040 2.43 0.356 0.0040 3.23 0.393 0.0040 4.46 0.466 0.0040 5.33 0.502 0.0040 6.54 0.566 0.0040 7.30 0.603 0.0040 8.43 0.657 0.0040 9.40 0.703 0.0040 10.34 0.739 0.0040 11.36 0.780 0.0040 12.34 0.808 0.0040 13.58 0.888 0.0040 14.53 0.992 0.0040 15.48 1.319 0.0040 16.52 1.327 0.0040 17.53 1.255 0.0040 18.53 1.238 0.0040 19.59 1.218 0.0040 20.60 1.220 0.0040 21.44 1.232 0.0040 22.53 1.087 0.0040 21.15 1.219 0.0040 20.34 1.241 0.0040 19.36 1.231 0.0040 18.29 1.235 0.0040 17.30 1.275 0.0040 16.31 1.343 0.0040 15.39 1.428 0.0040 14.39 1.479 0.0040 13.41 1.511 0.0040 12.44 1.500 0.0040 11.46 1.411 0.0040 10.37 1.270 0.0040 9.23 0.682 0.0040 8.09 0.631 0.0040 7.13 0.589 0.0040 6.04 0.531 0.0040 5.03 0.472 0.0040 4.03 0.428 0.0040 3.04 0.374 0.0040 1.91 0.316 0.0040 1.03 0.267 0.0040 0.05 0.209 0.0040 -1.02 0.157 0.0040 -2.13 0.090 0.0040 -3.01 0.018 0.0040 -4.00 -0.076 0.0040 -5.13 -0.209 0.0040 -6.04 -0.312 0.0040 Tabulated from data in file JG00195.DAT & reduced using program Q01.00L Average Reynolds #: 203200 Number of angles of attack: 57 alpha / Cl / Cm -6.05 -0.329 0.0040 -4.64 -0.159 0.0040 -3.63 -0.041 0.0040 -2.67 0.057 0.0040 -1.58 0.151 0.0040 -0.50 0.218 0.0040 0.25 0.262 0.0040 1.37 0.328 0.0040 2.39 0.385 0.0040 3.46 0.460 0.0040 4.45 0.531 0.0040 5.53 0.624 0.0040 6.34 0.774 0.0040 7.55 0.967 0.0040 8.55 1.101 0.0040 9.59 1.227 0.0040 10.43 1.322 0.0040 11.46 1.427 0.0040 12.44 1.491 0.0040 13.41 1.479 0.0040 14.39 1.420 0.0040 15.56 1.338 0.0040 16.52 1.291 0.0040 17.62 1.228 0.0040 18.42 1.212 0.0040 19.52 1.214 0.0040 20.45 1.214 0.0040 21.46 1.203 0.0040 22.36 1.151 0.0040 21.19 1.208 0.0040 20.20 1.213 0.0040 19.16 1.209 0.0040 18.24 1.215 0.0040 17.24 1.253 0.0040 16.32 1.304 0.0040 15.32 1.352 0.0040 14.33 1.419 0.0040 13.36 1.477 0.0040 12.40 1.484 0.0040 11.37 1.418 0.0040 10.34 1.310 0.0040 9.32 1.190 0.0040 8.32 1.067 0.0040 7.20 0.894 0.0040 5.99 0.719 0.0040 4.87 0.571 0.0040 3.93 0.479 0.0040 2.95 0.419 0.0040 1.86 0.348 0.0040 0.96 0.296 0.0040 -0.09 0.238 0.0040 -1.16 0.171 0.0040 -2.02 0.107 0.0040 -3.20 -0.007 0.0040 -4.10 -0.107 0.0040 -5.19 -0.238 0.0040 -6.14 -0.345 0.0040 Tabulated from data in file JG00196.DAT & reduced using program Q01.00L Average Reynolds #: 304200 Number of angles of attack: 57 alpha / Cl / Cm -6.03 -0.363 0.0040 -4.68 -0.203 0.0040 -3.83 -0.101 0.0040 -2.55 0.041 0.0040 -1.67 0.133 0.0040 -0.80 0.223 0.0040 0.42 0.350 0.0040 1.56 0.462 0.0040 2.43 0.545 0.0040 3.56 0.662 0.0040 4.41 0.751 0.0040 5.50 0.863 0.0040 6.46 0.963 0.0040 7.39 1.061 0.0040 8.43 1.171 0.0040 9.41 1.276 0.0040 10.48 1.388 0.0040 11.59 1.480 0.0040 12.49 1.511 0.0040 13.55 1.469 0.0040 14.53 1.399 0.0040 15.59 1.345 0.0040 16.50 1.299 0.0040 17.51 1.257 0.0040 18.62 1.241 0.0040 19.57 1.237 0.0040 20.72 1.233 0.0040 21.68 1.222 0.0040 22.52 1.230 0.0040 21.03 1.240 0.0040 20.09 1.244 0.0040 19.29 1.241 0.0040 18.15 1.244 0.0040 17.19 1.256 0.0040 16.32 1.308 0.0040 15.37 1.355 0.0040 14.32 1.410 0.0040 13.42 1.471 0.0040 12.39 1.509 0.0040 11.38 1.465 0.0040 10.39 1.379 0.0040 9.31 1.262 0.0040 8.28 1.151 0.0040 7.29 1.044 0.0040 6.21 0.932 0.0040 5.19 0.825 0.0040 4.13 0.712 0.0040 3.07 0.602 0.0040 1.86 0.477 0.0040 0.82 0.380 0.0040 -0.02 0.286 0.0040 -1.24 0.166 0.0040 -2.22 0.064 0.0040 -3.20 -0.042 0.0040 -4.11 -0.147 0.0040 -5.16 -0.279 0.0040 -6.13 -0.382 0.0040 Tabulated from data in file JG00198.DAT & reduced using program Q01.00L File m06b.lft created on 12-05-1997 at 15:25:50 using program FORMAT :::::::::::::: MA409.LFT :::::::::::::: Airfoil: MA409 Builder: R. Conney Comment: clean Number of Reynolds #'s: 6 Average Reynolds #: 30600 Number of angles of attack: 49 alpha / Cl / Cm -6.19 -0.431 -0.1150 -4.67 -0.315 -0.1150 -3.85 -0.253 -0.1150 -2.89 -0.177 -0.1150 -1.68 -0.073 -0.1150 -0.84 0.002 -0.1150 0.35 0.122 -0.1150 1.20 0.207 -0.1150 2.36 0.310 -0.1150 3.47 0.442 -0.1150 4.33 0.587 -0.1150 5.55 0.754 -0.1150 6.41 0.815 -0.1150 7.66 0.897 -0.1150 8.51 0.949 -0.1150 9.39 0.998 -0.1150 10.59 1.032 -0.1150 11.46 1.031 -0.1150 12.61 1.006 -0.1150 13.40 0.903 -0.1150 14.52 0.870 -0.1150 15.36 0.885 -0.1150 16.53 0.939 -0.1150 17.65 0.983 -0.1150 18.49 1.012 -0.1150 17.18 0.941 -0.1150 16.13 0.940 -0.1150 15.15 0.915 -0.1150 14.18 0.914 -0.1150 13.17 0.940 -0.1150 12.16 1.038 -0.1150 11.19 1.093 -0.1150 10.17 1.054 -0.1150 9.16 1.021 -0.1150 8.14 0.974 -0.1150 7.11 0.909 -0.1150 6.07 0.832 -0.1150 5.05 0.743 -0.1150 4.02 0.578 -0.1150 3.01 0.414 -0.1150 2.09 0.337 -0.1150 0.97 0.231 -0.1150 0.02 0.137 -0.1150 -1.07 0.036 -0.1150 -2.08 -0.049 -0.1150 -3.08 -0.142 -0.1150 -4.10 -0.230 -0.1150 -5.13 -0.329 -0.1150 -6.17 -0.414 -0.1150 Tabulated from data in file AB00524.DAT & reduced using program Q01.00L Average Reynolds #: 40400 Number of angles of attack: 49 alpha / Cl / Cm -5.85 -0.391 -0.1150 -4.65 -0.279 -0.1150 -3.74 -0.202 -0.1150 -2.82 -0.130 -0.1150 -1.60 -0.027 -0.1150 -0.73 0.052 -0.1150 0.47 0.170 -0.1150 1.41 0.262 -0.1150 2.25 0.334 -0.1150 3.44 0.539 -0.1150 4.35 0.673 -0.1150 5.55 0.781 -0.1150 6.43 0.832 -0.1150 7.39 0.900 -0.1150 8.62 0.970 -0.1150 9.52 1.007 -0.1150 10.41 1.041 -0.1150 11.60 1.067 -0.1150 12.45 1.001 -0.1150 13.55 0.931 -0.1150 14.39 0.910 -0.1150 15.55 0.910 -0.1150 16.42 0.928 -0.1150 17.58 0.933 -0.1150 18.47 1.021 -0.1150 17.12 0.940 -0.1150 16.07 0.918 -0.1150 15.07 0.965 -0.1150 14.26 0.963 -0.1150 13.11 1.010 -0.1150 12.25 1.008 -0.1150 11.18 1.069 -0.1150 10.19 1.048 -0.1150 9.16 1.014 -0.1150 8.15 0.976 -0.1150 7.15 0.919 -0.1150 6.17 0.832 -0.1150 5.21 0.785 -0.1150 4.08 0.672 -0.1150 3.11 0.497 -0.1150 2.00 0.337 -0.1150 1.01 0.252 -0.1150 0.04 0.159 -0.1150 -1.01 0.066 -0.1150 -2.12 -0.041 -0.1150 -3.14 -0.121 -0.1150 -4.16 -0.212 -0.1150 -5.21 -0.313 -0.1150 -6.25 -0.409 -0.1150 Tabulated from data in file AB00525.DAT & reduced using program Q01.00L Average Reynolds #: 61100 Number of angles of attack: 33 alpha / Cl / Cm -6.11 -0.385 -0.1150 -4.30 -0.228 -0.1150 -2.65 -0.100 -0.1150 -1.10 0.037 -0.1150 0.50 0.199 -0.1150 1.99 0.388 -0.1150 3.20 0.570 -0.1150 4.85 0.711 -0.1150 6.30 0.827 -0.1150 8.03 0.926 -0.1150 9.51 1.000 -0.1150 11.16 1.024 -0.1150 12.40 1.010 -0.1150 14.12 0.989 -0.1150 15.64 0.948 -0.1150 16.82 0.938 -0.1150 18.36 0.949 -0.1150 16.57 0.931 -0.1150 15.21 0.984 -0.1150 13.62 1.000 -0.1150 12.21 1.023 -0.1150 10.56 1.011 -0.1150 9.28 0.967 -0.1150 7.46 0.869 -0.1150 6.11 0.789 -0.1150 4.65 0.677 -0.1150 3.18 0.545 -0.1150 1.58 0.295 -0.1150 -0.19 0.118 -0.1150 -1.45 -0.002 -0.1150 -3.17 -0.140 -0.1150 -4.69 -0.257 -0.1150 -6.05 -0.391 -0.1150 Tabulated from data in file MS00176.DAT & reduced using program Q01.00L Average Reynolds #: 101800 Number of angles of attack: 33 alpha / Cl / Cm -6.11 -0.407 -0.1150 -4.37 -0.228 -0.1150 -2.57 -0.086 -0.1150 -1.26 0.029 -0.1150 0.38 0.190 -0.1150 1.78 0.416 -0.1150 3.36 0.587 -0.1150 5.10 0.737 -0.1150 6.38 0.836 -0.1150 8.21 0.948 -0.1150 9.49 1.014 -0.1150 11.15 1.048 -0.1150 12.30 1.012 -0.1150 14.03 0.952 -0.1150 15.73 0.935 -0.1150 17.03 0.922 -0.1150 18.24 0.907 -0.1150 16.83 0.932 -0.1150 15.21 0.958 -0.1150 13.55 0.974 -0.1150 12.16 0.998 -0.1150 10.76 1.037 -0.1150 9.14 0.974 -0.1150 7.69 0.894 -0.1150 6.25 0.804 -0.1150 4.49 0.663 -0.1150 2.99 0.531 -0.1150 1.60 0.386 -0.1150 -0.01 0.143 -0.1150 -1.74 -0.024 -0.1150 -3.17 -0.141 -0.1150 -4.65 -0.259 -0.1150 -6.19 -0.422 -0.1150 Tabulated from data in file JG00178.DAT & reduced using program Q01.00L Average Reynolds #: 203000 Number of angles of attack: 33 alpha / Cl / Cm -5.95 -0.397 -0.1150 -4.40 -0.240 -0.1150 -2.89 -0.116 -0.1150 -1.40 0.056 -0.1150 -0.07 0.221 -0.1150 1.69 0.405 -0.1150 3.26 0.563 -0.1150 4.64 0.689 -0.1150 6.17 0.819 -0.1150 7.63 0.920 -0.1150 9.20 1.009 -0.1150 10.64 1.070 -0.1150 12.20 1.069 -0.1150 13.63 1.036 -0.1150 15.02 0.995 -0.1150 16.59 0.964 -0.1150 18.06 0.941 -0.1150 16.63 0.950 -0.1150 15.16 1.007 -0.1150 13.78 1.050 -0.1150 12.20 1.071 -0.1150 10.92 1.080 -0.1150 9.49 1.020 -0.1150 7.88 0.930 -0.1150 6.32 0.824 -0.1150 4.80 0.695 -0.1150 3.36 0.564 -0.1150 1.78 0.411 -0.1150 0.07 0.231 -0.1150 -1.30 0.063 -0.1150 -2.88 -0.120 -0.1150 -4.49 -0.251 -0.1150 -5.91 -0.399 -0.1150 Tabulated from data in file AB00180.DAT & reduced using program Q01.00L Average Reynolds #: 304000 Number of angles of attack: 33 alpha / Cl / Cm -6.09 -0.406 -0.1150 -4.67 -0.268 -0.1150 -3.19 -0.140 -0.1150 -1.58 0.050 -0.1150 -0.02 0.232 -0.1150 1.43 0.379 -0.1150 3.38 0.570 -0.1150 4.87 0.703 -0.1150 6.28 0.822 -0.1150 7.95 0.945 -0.1150 9.34 1.025 -0.1150 10.80 1.089 -0.1150 11.99 1.091 -0.1150 13.45 1.053 -0.1150 14.97 0.997 -0.1150 16.61 0.988 -0.1150 18.00 0.996 -0.1150 16.80 1.005 -0.1150 15.29 1.005 -0.1150 13.79 1.030 -0.1150 12.39 1.095 -0.1150 11.04 1.084 -0.1150 9.38 1.026 -0.1150 7.83 0.935 -0.1150 6.36 0.828 -0.1150 4.64 0.681 -0.1150 3.15 0.540 -0.1150 1.53 0.383 -0.1150 0.08 0.234 -0.1150 -1.45 0.060 -0.1150 -3.04 -0.132 -0.1150 -4.68 -0.276 -0.1150 -5.94 -0.399 -0.1150 Tabulated from data in file AB00182.DAT & reduced using program Q01.00L File ma409.lft created on 12-05-1997 at 15:25:50 using program FORMAT :::::::::::::: MB253515.LFT :::::::::::::: Airfoil: MB253515 Builder: M. Bame Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 20100 Number of angles of attack: 97 alpha / Cl / Cm -6.18 -0.599 -0.0500 -5.33 -0.464 -0.0500 -5.01 -0.435 -0.0500 -4.38 -0.319 -0.0500 -3.85 -0.244 -0.0500 -3.24 -0.217 -0.0500 -2.90 -0.186 -0.0500 -2.27 -0.167 -0.0500 -1.84 -0.153 -0.0500 -1.25 -0.112 -0.0500 -0.81 -0.108 -0.0500 -0.24 -0.031 -0.0500 0.26 -0.006 -0.0500 0.67 -0.005 -0.0500 1.12 0.007 -0.0500 1.76 0.071 -0.0500 2.18 0.132 -0.0500 2.81 0.167 -0.0500 3.25 0.184 -0.0500 3.84 0.222 -0.0500 4.27 0.278 -0.0500 4.91 0.296 -0.0500 5.19 0.352 -0.0500 5.86 0.334 -0.0500 6.24 0.354 -0.0500 6.92 0.415 -0.0500 7.34 0.419 -0.0500 7.99 0.440 -0.0500 8.28 0.499 -0.0500 8.87 0.494 -0.0500 9.36 0.561 -0.0500 9.99 0.533 -0.0500 10.22 0.541 -0.0500 10.98 0.570 -0.0500 11.28 0.626 -0.0500 11.80 0.603 -0.0500 12.30 0.657 -0.0500 12.99 0.645 -0.0500 13.36 0.646 -0.0500 13.92 0.712 -0.0500 14.33 0.722 -0.0500 14.88 0.716 -0.0500 15.31 0.718 -0.0500 15.86 0.778 -0.0500 16.32 0.823 -0.0500 17.01 0.849 -0.0500 17.41 0.840 -0.0500 17.95 0.851 -0.0500 18.40 0.868 -0.0500 17.82 0.857 -0.0500 17.32 0.784 -0.0500 16.80 0.741 -0.0500 16.31 0.704 -0.0500 15.74 0.662 -0.0500 15.27 0.635 -0.0500 14.73 0.615 -0.0500 14.27 0.611 -0.0500 13.76 0.608 -0.0500 13.22 0.586 -0.0500 12.74 0.560 -0.0500 12.21 0.533 -0.0500 11.72 0.521 -0.0500 11.19 0.503 -0.0500 10.70 0.517 -0.0500 10.16 0.468 -0.0500 9.63 0.446 -0.0500 9.19 0.429 -0.0500 8.70 0.398 -0.0500 8.13 0.347 -0.0500 7.64 0.333 -0.0500 7.17 0.316 -0.0500 6.66 0.291 -0.0500 6.17 0.235 -0.0500 5.58 0.201 -0.0500 5.11 0.153 -0.0500 4.66 0.185 -0.0500 4.10 0.128 -0.0500 3.57 0.111 -0.0500 3.09 0.063 -0.0500 2.51 0.025 -0.0500 2.03 -0.016 -0.0500 1.58 -0.047 -0.0500 1.03 -0.097 -0.0500 0.51 -0.130 -0.0500 0.00 -0.162 -0.0500 -0.52 -0.193 -0.0500 -1.01 -0.219 -0.0500 -1.54 -0.232 -0.0500 -2.02 -0.251 -0.0500 -2.48 -0.263 -0.0500 -2.98 -0.296 -0.0500 -3.55 -0.318 -0.0500 -4.05 -0.344 -0.0500 -4.52 -0.371 -0.0500 -5.11 -0.509 -0.0500 -5.61 -0.532 -0.0500 -6.17 -0.612 -0.0500 Tabulated from data in file MS00367.DAT & reduced using program Q01.00L Average Reynolds #: 41600 Number of angles of attack: 97 alpha / Cl / Cm -6.16 -0.473 -0.0500 -5.41 -0.442 -0.0500 -4.93 -0.412 -0.0500 -4.36 -0.370 -0.0500 -3.82 -0.292 -0.0500 -3.42 -0.258 -0.0500 -2.81 -0.207 -0.0500 -2.39 -0.171 -0.0500 -1.84 -0.118 -0.0500 -1.43 -0.113 -0.0500 -0.94 -0.074 -0.0500 -0.31 -0.036 -0.0500 0.19 0.020 -0.0500 0.63 0.053 -0.0500 1.28 0.097 -0.0500 1.68 0.121 -0.0500 2.23 0.157 -0.0500 2.82 0.204 -0.0500 3.16 0.212 -0.0500 3.78 0.239 -0.0500 4.30 0.270 -0.0500 4.88 0.303 -0.0500 5.29 0.328 -0.0500 5.93 0.370 -0.0500 6.18 0.385 -0.0500 6.80 0.384 -0.0500 7.20 0.388 -0.0500 7.85 0.421 -0.0500 8.29 0.435 -0.0500 8.92 0.460 -0.0500 9.31 0.474 -0.0500 9.91 0.501 -0.0500 10.30 0.495 -0.0500 10.84 0.538 -0.0500 11.26 0.545 -0.0500 11.75 0.562 -0.0500 12.36 0.712 -0.0500 12.93 0.809 -0.0500 13.32 0.843 -0.0500 14.12 1.136 -0.0500 14.49 1.104 -0.0500 15.07 1.093 -0.0500 15.48 1.070 -0.0500 16.05 1.109 -0.0500 16.47 1.125 -0.0500 17.01 1.123 -0.0500 17.43 1.107 -0.0500 17.95 1.095 -0.0500 18.46 1.129 -0.0500 17.82 0.936 -0.0500 17.33 0.955 -0.0500 16.82 1.050 -0.0500 16.37 1.076 -0.0500 15.88 1.070 -0.0500 15.32 1.048 -0.0500 14.80 1.060 -0.0500 14.35 1.072 -0.0500 13.88 1.093 -0.0500 13.34 1.091 -0.0500 12.83 1.101 -0.0500 12.38 1.085 -0.0500 11.81 1.082 -0.0500 11.35 1.064 -0.0500 10.84 1.020 -0.0500 10.21 0.529 -0.0500 9.69 0.456 -0.0500 9.17 0.432 -0.0500 8.60 0.421 -0.0500 8.18 0.409 -0.0500 7.70 0.382 -0.0500 7.21 0.365 -0.0500 6.68 0.344 -0.0500 6.17 0.322 -0.0500 5.60 0.307 -0.0500 5.10 0.286 -0.0500 4.59 0.259 -0.0500 4.14 0.232 -0.0500 3.58 0.212 -0.0500 3.11 0.187 -0.0500 2.65 0.158 -0.0500 2.11 0.129 -0.0500 1.54 0.085 -0.0500 1.06 0.038 -0.0500 0.54 0.007 -0.0500 0.14 -0.029 -0.0500 -0.47 -0.085 -0.0500 -1.01 -0.130 -0.0500 -1.46 -0.155 -0.0500 -1.94 -0.178 -0.0500 -2.47 -0.238 -0.0500 -2.95 -0.275 -0.0500 -3.54 -0.331 -0.0500 -4.07 -0.396 -0.0500 -4.56 -0.427 -0.0500 -5.02 -0.452 -0.0500 -5.56 -0.469 -0.0500 -6.08 -0.496 -0.0500 Tabulated from data in file MS00366.DAT & reduced using program Q01.00L Average Reynolds #: 61400 Number of angles of attack: 97 alpha / Cl / Cm -6.15 -0.488 -0.0500 -5.50 -0.417 -0.0500 -4.88 -0.356 -0.0500 -4.40 -0.324 -0.0500 -3.99 -0.285 -0.0500 -3.45 -0.252 -0.0500 -2.95 -0.224 -0.0500 -2.38 -0.130 -0.0500 -1.90 -0.023 -0.0500 -1.36 0.038 -0.0500 -0.94 0.053 -0.0500 -0.39 0.036 -0.0500 0.09 0.056 -0.0500 0.69 0.100 -0.0500 1.23 0.139 -0.0500 1.78 0.181 -0.0500 2.16 0.211 -0.0500 2.71 0.219 -0.0500 3.21 0.244 -0.0500 3.76 0.289 -0.0500 4.18 0.328 -0.0500 4.75 0.370 -0.0500 5.22 0.390 -0.0500 5.83 0.407 -0.0500 6.17 0.423 -0.0500 6.93 0.447 -0.0500 7.25 0.446 -0.0500 7.78 0.461 -0.0500 8.22 0.492 -0.0500 8.94 0.514 -0.0500 9.31 0.520 -0.0500 9.81 0.545 -0.0500 10.22 0.563 -0.0500 10.82 0.613 -0.0500 11.33 0.647 -0.0500 11.80 0.679 -0.0500 12.33 0.740 -0.0500 13.03 1.035 -0.0500 13.37 1.042 -0.0500 13.97 1.052 -0.0500 14.34 1.060 -0.0500 14.89 1.064 -0.0500 15.41 1.071 -0.0500 16.03 1.072 -0.0500 16.37 1.074 -0.0500 16.96 1.055 -0.0500 17.32 1.030 -0.0500 17.86 1.000 -0.0500 18.34 1.008 -0.0500 17.86 0.980 -0.0500 17.35 1.055 -0.0500 16.88 1.048 -0.0500 16.35 1.059 -0.0500 15.82 1.058 -0.0500 15.31 1.055 -0.0500 14.86 1.057 -0.0500 14.35 1.047 -0.0500 13.87 1.040 -0.0500 13.35 1.033 -0.0500 12.89 1.039 -0.0500 12.34 1.057 -0.0500 11.85 1.076 -0.0500 11.36 1.091 -0.0500 10.85 1.090 -0.0500 10.33 1.082 -0.0500 9.86 1.049 -0.0500 9.18 0.511 -0.0500 8.67 0.495 -0.0500 8.18 0.483 -0.0500 7.64 0.458 -0.0500 7.22 0.460 -0.0500 6.70 0.432 -0.0500 6.15 0.428 -0.0500 5.71 0.422 -0.0500 5.22 0.391 -0.0500 4.67 0.363 -0.0500 4.19 0.318 -0.0500 3.62 0.280 -0.0500 3.17 0.258 -0.0500 2.64 0.244 -0.0500 2.17 0.204 -0.0500 1.61 0.177 -0.0500 1.13 0.136 -0.0500 0.59 0.101 -0.0500 0.12 0.055 -0.0500 -0.39 0.044 -0.0500 -0.93 0.056 -0.0500 -1.42 0.034 -0.0500 -1.97 -0.045 -0.0500 -2.44 -0.151 -0.0500 -3.02 -0.240 -0.0500 -3.55 -0.259 -0.0500 -3.97 -0.280 -0.0500 -4.54 -0.337 -0.0500 -5.04 -0.380 -0.0500 -5.59 -0.437 -0.0500 -6.09 -0.484 -0.0500 Tabulated from data in file MS00365.DAT & reduced using program Q01.00L Average Reynolds #: 81600 Number of angles of attack: 97 alpha / Cl / Cm -5.84 -0.387 -0.0500 -5.32 -0.340 -0.0500 -4.70 -0.292 -0.0500 -4.37 -0.267 -0.0500 -3.81 -0.229 -0.0500 -3.37 -0.189 -0.0500 -2.83 -0.158 -0.0500 -2.19 -0.073 -0.0500 -1.90 -0.039 -0.0500 -1.25 0.071 -0.0500 -0.86 0.125 -0.0500 -0.15 0.128 -0.0500 0.17 0.143 -0.0500 0.81 0.159 -0.0500 1.32 0.184 -0.0500 1.72 0.200 -0.0500 2.15 0.219 -0.0500 2.79 0.247 -0.0500 3.17 0.269 -0.0500 3.84 0.306 -0.0500 4.29 0.330 -0.0500 4.91 0.364 -0.0500 5.19 0.395 -0.0500 5.84 0.400 -0.0500 6.31 0.464 -0.0500 7.00 0.488 -0.0500 7.24 0.471 -0.0500 7.87 0.509 -0.0500 8.37 0.522 -0.0500 9.04 0.549 -0.0500 9.27 0.558 -0.0500 9.87 0.570 -0.0500 10.30 0.620 -0.0500 10.97 1.070 -0.0500 11.43 1.053 -0.0500 11.88 1.039 -0.0500 12.35 1.027 -0.0500 13.01 1.023 -0.0500 13.39 1.026 -0.0500 14.08 1.040 -0.0500 14.43 1.033 -0.0500 14.92 1.040 -0.0500 15.35 1.038 -0.0500 16.05 1.036 -0.0500 16.40 1.037 -0.0500 16.89 1.036 -0.0500 17.38 1.023 -0.0500 18.05 1.025 -0.0500 18.44 0.968 -0.0500 17.84 1.030 -0.0500 17.36 1.028 -0.0500 16.86 1.029 -0.0500 16.31 1.035 -0.0500 15.90 1.038 -0.0500 15.34 1.038 -0.0500 14.89 1.034 -0.0500 14.36 1.028 -0.0500 13.86 1.025 -0.0500 13.32 1.018 -0.0500 12.86 1.014 -0.0500 12.31 1.020 -0.0500 11.88 1.027 -0.0500 11.35 1.046 -0.0500 10.85 1.063 -0.0500 10.34 1.072 -0.0500 9.83 1.064 -0.0500 9.35 1.020 -0.0500 8.79 0.971 -0.0500 8.35 0.934 -0.0500 7.80 0.884 -0.0500 7.21 0.456 -0.0500 6.69 0.457 -0.0500 6.23 0.420 -0.0500 5.60 0.406 -0.0500 5.16 0.368 -0.0500 4.67 0.348 -0.0500 4.15 0.323 -0.0500 3.59 0.269 -0.0500 3.11 0.252 -0.0500 2.66 0.233 -0.0500 2.16 0.209 -0.0500 1.61 0.192 -0.0500 1.06 0.175 -0.0500 0.62 0.161 -0.0500 0.11 0.133 -0.0500 -0.41 0.137 -0.0500 -0.90 0.106 -0.0500 -1.43 0.035 -0.0500 -1.96 -0.047 -0.0500 -2.44 -0.100 -0.0500 -2.97 -0.144 -0.0500 -3.49 -0.196 -0.0500 -4.00 -0.254 -0.0500 -4.50 -0.281 -0.0500 -4.98 -0.313 -0.0500 -5.52 -0.359 -0.0500 -6.10 -0.426 -0.0500 Tabulated from data in file MS00368.DAT & reduced using program Q01.00L Average Reynolds #: 101400 Number of angles of attack: 97 alpha / Cl / Cm -6.18 -0.373 -0.0500 -5.20 -0.271 -0.0500 -4.95 -0.255 -0.0500 -4.21 -0.216 -0.0500 -3.79 -0.191 -0.0500 -3.26 -0.104 -0.0500 -2.87 -0.085 -0.0500 -2.31 -0.063 -0.0500 -1.75 -0.020 -0.0500 -1.25 0.049 -0.0500 -0.67 0.174 -0.0500 -0.11 0.286 -0.0500 0.23 0.343 -0.0500 0.79 0.364 -0.0500 1.25 0.370 -0.0500 1.93 0.373 -0.0500 2.20 0.380 -0.0500 2.91 0.424 -0.0500 3.19 0.471 -0.0500 3.94 0.545 -0.0500 4.20 0.589 -0.0500 4.92 0.670 -0.0500 5.28 0.712 -0.0500 6.01 0.781 -0.0500 6.30 0.809 -0.0500 7.03 0.878 -0.0500 7.37 0.908 -0.0500 8.08 0.969 -0.0500 8.39 0.994 -0.0500 9.06 1.050 -0.0500 9.42 1.090 -0.0500 10.09 1.083 -0.0500 10.42 1.081 -0.0500 10.98 1.059 -0.0500 11.50 1.044 -0.0500 12.11 1.031 -0.0500 12.38 1.027 -0.0500 12.95 1.029 -0.0500 13.42 1.035 -0.0500 14.00 1.038 -0.0500 14.47 1.043 -0.0500 15.05 1.053 -0.0500 15.50 1.056 -0.0500 16.11 1.053 -0.0500 16.38 1.049 -0.0500 16.93 1.037 -0.0500 17.44 1.023 -0.0500 18.03 1.010 -0.0500 18.36 0.972 -0.0500 17.70 1.015 -0.0500 17.31 1.020 -0.0500 16.81 1.018 -0.0500 16.38 1.036 -0.0500 15.85 1.035 -0.0500 15.34 1.036 -0.0500 14.80 1.029 -0.0500 14.35 1.025 -0.0500 13.83 1.020 -0.0500 13.37 1.013 -0.0500 12.89 1.005 -0.0500 12.33 1.003 -0.0500 11.81 1.011 -0.0500 11.36 1.025 -0.0500 10.80 1.050 -0.0500 10.36 1.060 -0.0500 9.81 1.071 -0.0500 9.32 1.057 -0.0500 8.82 1.005 -0.0500 8.35 0.963 -0.0500 7.81 0.921 -0.0500 7.35 0.881 -0.0500 6.77 0.827 -0.0500 6.24 0.778 -0.0500 5.66 0.716 -0.0500 5.24 0.669 -0.0500 4.68 0.605 -0.0500 4.26 0.563 -0.0500 3.71 0.484 -0.0500 3.15 0.428 -0.0500 2.62 0.388 -0.0500 2.20 0.369 -0.0500 1.68 0.365 -0.0500 1.15 0.349 -0.0500 0.64 0.328 -0.0500 0.10 0.303 -0.0500 -0.43 0.200 -0.0500 -0.90 0.116 -0.0500 -1.39 0.018 -0.0500 -1.95 -0.053 -0.0500 -2.45 -0.086 -0.0500 -2.95 -0.094 -0.0500 -3.48 -0.133 -0.0500 -4.00 -0.209 -0.0500 -4.50 -0.232 -0.0500 -5.01 -0.262 -0.0500 -5.49 -0.289 -0.0500 -6.14 -0.357 -0.0500 Tabulated from data in file MS00369.DAT & reduced using program Q01.00L File mb253515.lft created on 12-05-1997 at 15:25:50 using program FORMAT :::::::::::::: MH45.LFT :::::::::::::: Airfoil: MH45 Builder: C. Fox Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 61400 Number of angles of attack: 33 alpha / Cl / Cm -6.14 -0.419 -0.0060 -4.73 -0.295 -0.0060 -3.19 -0.165 -0.0060 -1.62 0.040 -0.0060 -0.06 0.254 -0.0060 1.46 0.396 -0.0060 2.98 0.521 -0.0060 4.52 0.653 -0.0060 6.03 0.778 -0.0060 7.59 0.902 -0.0060 9.10 1.004 -0.0060 10.65 1.088 -0.0060 12.12 1.119 -0.0060 13.54 0.774 -0.0060 15.07 0.783 -0.0060 16.58 0.857 -0.0060 18.11 0.893 -0.0060 16.85 0.887 -0.0060 15.25 0.828 -0.0060 13.81 0.786 -0.0060 12.23 0.740 -0.0060 10.79 0.850 -0.0060 9.32 0.993 -0.0060 7.82 0.904 -0.0060 6.23 0.779 -0.0060 4.79 0.659 -0.0060 3.18 0.524 -0.0060 1.65 0.396 -0.0060 0.12 0.259 -0.0060 -1.40 0.060 -0.0060 -2.99 -0.150 -0.0060 -4.49 -0.275 -0.0060 -6.09 -0.402 -0.0060 Tabulated from data in file MS00111.DAT & reduced using program Q01.00L Average Reynolds #: 102100 Number of angles of attack: 33 alpha / Cl / Cm -6.20 -0.463 -0.0060 -4.58 -0.326 -0.0060 -2.99 -0.154 -0.0060 -1.41 0.074 -0.0060 0.18 0.213 -0.0060 1.49 0.328 -0.0060 3.18 0.483 -0.0060 4.68 0.629 -0.0060 6.18 0.772 -0.0060 7.68 0.905 -0.0060 9.25 1.013 -0.0060 10.69 1.090 -0.0060 12.37 1.104 -0.0060 13.90 1.069 -0.0060 15.24 0.806 -0.0060 16.87 0.831 -0.0060 18.23 0.878 -0.0060 16.62 0.822 -0.0060 15.09 0.782 -0.0060 13.70 0.800 -0.0060 12.19 0.842 -0.0060 10.68 1.091 -0.0060 9.22 1.010 -0.0060 7.64 0.894 -0.0060 6.09 0.761 -0.0060 4.57 0.615 -0.0060 3.08 0.472 -0.0060 1.64 0.340 -0.0060 0.05 0.202 -0.0060 -1.57 0.057 -0.0060 -3.08 -0.164 -0.0060 -4.60 -0.323 -0.0060 -6.09 -0.444 -0.0060 Tabulated from data in file JG00113.DAT & reduced using program Q01.00L Average Reynolds #: 203700 Number of angles of attack: 33 alpha / Cl / Cm -6.13 -0.450 -0.0060 -4.65 -0.304 -0.0060 -3.08 -0.162 -0.0060 -1.63 -0.028 -0.0060 -0.02 0.166 -0.0060 1.50 0.319 -0.0060 3.26 0.506 -0.0060 4.66 0.652 -0.0060 6.12 0.800 -0.0060 7.74 0.946 -0.0060 9.27 1.065 -0.0060 10.67 1.146 -0.0060 12.26 1.132 -0.0060 13.68 1.097 -0.0060 15.30 1.049 -0.0060 16.74 0.953 -0.0060 18.23 0.871 -0.0060 16.63 0.951 -0.0060 15.14 0.930 -0.0060 13.26 0.908 -0.0060 12.13 1.133 -0.0060 10.74 1.142 -0.0060 9.31 1.063 -0.0060 7.65 0.931 -0.0060 6.14 0.793 -0.0060 4.55 0.633 -0.0060 3.04 0.474 -0.0060 1.52 0.314 -0.0060 0.01 0.162 -0.0060 -1.50 -0.021 -0.0060 -3.11 -0.168 -0.0060 -4.62 -0.305 -0.0060 -6.11 -0.452 -0.0060 Tabulated from data in file JG00115.DAT & reduced using program Q01.00L Average Reynolds #: 304900 Number of angles of attack: 33 alpha / Cl / Cm -6.81 -0.536 -0.0060 -3.94 -0.267 -0.0060 -2.97 -0.173 -0.0060 -1.45 -0.023 -0.0060 0.16 0.168 -0.0060 1.46 0.311 -0.0060 3.04 0.489 -0.0060 4.50 0.644 -0.0060 6.26 0.825 -0.0060 7.68 0.959 -0.0060 9.35 1.099 -0.0060 10.77 1.177 -0.0060 12.31 1.145 -0.0060 13.68 1.115 -0.0060 15.34 1.074 -0.0060 16.38 1.079 -0.0060 18.09 0.957 -0.0060 16.73 1.053 -0.0060 15.28 1.069 -0.0060 13.76 1.112 -0.0060 12.22 1.161 -0.0060 10.75 1.175 -0.0060 9.26 1.089 -0.0060 7.66 0.955 -0.0060 6.13 0.808 -0.0060 4.61 0.651 -0.0060 3.11 0.489 -0.0060 1.48 0.308 -0.0060 0.01 0.147 -0.0060 -1.55 -0.036 -0.0060 -3.15 -0.196 -0.0060 -4.77 -0.350 -0.0060 -6.25 -0.486 -0.0060 Tabulated from data in file JG00117.DAT & reduced using program Q01.00L File mh45.lft created on 12-05-1997 at 15:25:50 using program FORMAT :::::::::::::: N0009.LFT :::::::::::::: Airfoil: NACA 0009 Builder: M. Nankivil Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 40600 Number of angles of attack: 97 alpha / Cl / Cm -6.13 -0.527 0.0000 -5.50 -0.490 0.0000 -5.01 -0.456 0.0000 -4.48 -0.419 0.0000 -4.00 -0.389 0.0000 -3.46 -0.322 0.0000 -3.03 -0.248 0.0000 -2.35 -0.126 0.0000 -1.96 -0.099 0.0000 -1.40 -0.061 0.0000 -0.96 -0.036 0.0000 -0.38 0.002 0.0000 0.07 0.035 0.0000 0.65 0.075 0.0000 1.10 0.106 0.0000 1.67 0.151 0.0000 2.11 0.198 0.0000 2.75 0.282 0.0000 3.16 0.340 0.0000 3.75 0.443 0.0000 4.20 0.496 0.0000 4.74 0.535 0.0000 5.22 0.571 0.0000 5.71 0.601 0.0000 6.21 0.637 0.0000 6.79 0.673 0.0000 7.28 0.703 0.0000 7.80 0.740 0.0000 8.26 0.762 0.0000 8.88 0.795 0.0000 9.26 0.831 0.0000 9.73 0.829 0.0000 10.30 0.852 0.0000 10.70 0.800 0.0000 11.29 0.759 0.0000 11.71 0.786 0.0000 12.24 0.733 0.0000 12.75 0.713 0.0000 13.28 0.721 0.0000 13.81 0.686 0.0000 14.23 0.689 0.0000 14.77 0.697 0.0000 15.28 0.689 0.0000 15.78 0.729 0.0000 16.24 0.731 0.0000 16.86 0.735 0.0000 17.23 0.747 0.0000 17.68 0.748 0.0000 18.29 0.766 0.0000 17.88 0.735 0.0000 17.43 0.744 0.0000 16.97 0.717 0.0000 16.40 0.725 0.0000 15.91 0.707 0.0000 15.37 0.693 0.0000 14.85 0.678 0.0000 14.41 0.673 0.0000 13.93 0.698 0.0000 13.36 0.683 0.0000 12.86 0.676 0.0000 12.41 0.723 0.0000 11.96 0.724 0.0000 11.34 0.744 0.0000 10.84 0.741 0.0000 10.39 0.765 0.0000 9.98 0.788 0.0000 9.40 0.806 0.0000 8.87 0.780 0.0000 8.31 0.746 0.0000 7.81 0.716 0.0000 7.31 0.689 0.0000 6.82 0.660 0.0000 6.39 0.628 0.0000 5.90 0.596 0.0000 5.27 0.559 0.0000 4.79 0.529 0.0000 4.36 0.498 0.0000 3.81 0.436 0.0000 3.23 0.337 0.0000 2.83 0.274 0.0000 2.21 0.215 0.0000 1.71 0.156 0.0000 1.18 0.106 0.0000 0.75 0.073 0.0000 0.25 0.038 0.0000 -0.25 0.005 0.0000 -0.86 -0.029 0.0000 -1.25 -0.056 0.0000 -1.82 -0.092 0.0000 -2.29 -0.126 0.0000 -2.91 -0.199 0.0000 -3.35 -0.268 0.0000 -3.97 -0.356 0.0000 -4.35 -0.394 0.0000 -4.86 -0.436 0.0000 -5.40 -0.472 0.0000 -5.92 -0.512 0.0000 Tabulated from data in file MS00279.DAT & reduced using program Q01.00L Average Reynolds #: 60900 Number of angles of attack: 97 alpha / Cl / Cm -6.12 -0.520 0.0000 -5.46 -0.471 0.0000 -5.09 -0.452 0.0000 -4.43 -0.409 0.0000 -4.06 -0.381 0.0000 -3.43 -0.322 0.0000 -3.04 -0.275 0.0000 -2.39 -0.176 0.0000 -1.98 -0.115 0.0000 -1.39 -0.060 0.0000 -0.93 -0.032 0.0000 -0.30 0.000 0.0000 0.08 0.020 0.0000 0.64 0.056 0.0000 1.06 0.090 0.0000 1.69 0.151 0.0000 2.11 0.223 0.0000 2.75 0.339 0.0000 3.16 0.377 0.0000 3.78 0.431 0.0000 4.14 0.463 0.0000 4.67 0.506 0.0000 5.20 0.548 0.0000 5.80 0.592 0.0000 6.22 0.623 0.0000 6.75 0.659 0.0000 7.24 0.693 0.0000 7.75 0.724 0.0000 8.22 0.752 0.0000 8.72 0.782 0.0000 9.27 0.805 0.0000 9.70 0.811 0.0000 10.26 0.837 0.0000 10.82 0.834 0.0000 11.27 0.830 0.0000 11.83 0.796 0.0000 12.27 0.763 0.0000 12.73 0.761 0.0000 13.29 0.733 0.0000 13.82 0.731 0.0000 14.24 0.731 0.0000 14.85 0.723 0.0000 15.20 0.704 0.0000 15.82 0.739 0.0000 16.27 0.795 0.0000 16.70 0.727 0.0000 17.24 0.767 0.0000 17.87 0.784 0.0000 18.26 0.772 0.0000 17.83 0.816 0.0000 17.29 0.763 0.0000 16.79 0.758 0.0000 16.33 0.726 0.0000 15.80 0.734 0.0000 15.29 0.749 0.0000 14.86 0.737 0.0000 14.28 0.745 0.0000 13.83 0.732 0.0000 13.37 0.741 0.0000 12.81 0.732 0.0000 12.37 0.763 0.0000 11.84 0.793 0.0000 11.34 0.787 0.0000 10.93 0.823 0.0000 10.42 0.806 0.0000 9.86 0.804 0.0000 9.34 0.792 0.0000 8.86 0.771 0.0000 8.30 0.742 0.0000 7.83 0.714 0.0000 7.25 0.679 0.0000 6.82 0.648 0.0000 6.33 0.615 0.0000 5.83 0.576 0.0000 5.26 0.537 0.0000 4.88 0.507 0.0000 4.24 0.454 0.0000 3.73 0.414 0.0000 3.25 0.372 0.0000 2.83 0.320 0.0000 2.21 0.225 0.0000 1.80 0.148 0.0000 1.20 0.078 0.0000 0.72 0.045 0.0000 0.13 0.007 0.0000 -0.28 -0.018 0.0000 -0.82 -0.050 0.0000 -1.25 -0.071 0.0000 -1.88 -0.117 0.0000 -2.38 -0.191 0.0000 -2.82 -0.265 0.0000 -3.34 -0.328 0.0000 -3.99 -0.386 0.0000 -4.38 -0.416 0.0000 -4.86 -0.450 0.0000 -5.40 -0.484 0.0000 -6.00 -0.527 0.0000 Tabulated from data in file MS00280.DAT & reduced using program Q01.00L Average Reynolds #: 79900 Number of angles of attack: 97 alpha / Cl / Cm -6.17 -0.551 0.0000 -5.57 -0.508 0.0000 -5.10 -0.471 0.0000 -4.47 -0.428 0.0000 -4.11 -0.406 0.0000 -3.47 -0.346 0.0000 -3.05 -0.307 0.0000 -2.55 -0.249 0.0000 -1.99 -0.159 0.0000 -1.41 -0.073 0.0000 -0.97 -0.045 0.0000 -0.34 -0.017 0.0000 0.07 0.006 0.0000 0.54 0.034 0.0000 1.02 0.072 0.0000 1.55 0.158 0.0000 2.11 0.266 0.0000 2.60 0.299 0.0000 3.16 0.352 0.0000 3.67 0.409 0.0000 4.13 0.448 0.0000 4.77 0.501 0.0000 5.15 0.532 0.0000 5.70 0.574 0.0000 6.18 0.613 0.0000 6.75 0.655 0.0000 7.16 0.682 0.0000 7.67 0.717 0.0000 8.22 0.751 0.0000 8.80 0.783 0.0000 9.21 0.803 0.0000 9.73 0.807 0.0000 10.27 0.827 0.0000 10.79 0.838 0.0000 11.23 0.804 0.0000 11.79 0.800 0.0000 12.24 0.787 0.0000 12.72 0.777 0.0000 13.25 0.773 0.0000 13.80 0.754 0.0000 14.19 0.740 0.0000 14.76 0.724 0.0000 15.19 0.723 0.0000 15.72 0.730 0.0000 16.19 0.722 0.0000 16.79 0.784 0.0000 17.22 0.788 0.0000 17.80 0.782 0.0000 18.24 0.757 0.0000 17.94 0.849 0.0000 17.37 0.780 0.0000 16.75 0.739 0.0000 16.38 0.738 0.0000 15.87 0.742 0.0000 15.34 0.737 0.0000 14.85 0.734 0.0000 14.36 0.752 0.0000 13.89 0.751 0.0000 13.37 0.771 0.0000 12.91 0.766 0.0000 12.39 0.811 0.0000 11.95 0.790 0.0000 11.38 0.813 0.0000 10.97 0.823 0.0000 10.40 0.832 0.0000 9.85 0.841 0.0000 9.41 0.813 0.0000 8.95 0.786 0.0000 8.35 0.752 0.0000 7.89 0.725 0.0000 7.32 0.687 0.0000 6.86 0.654 0.0000 6.29 0.616 0.0000 5.84 0.579 0.0000 5.32 0.539 0.0000 4.86 0.504 0.0000 4.28 0.457 0.0000 3.77 0.408 0.0000 3.22 0.347 0.0000 2.78 0.300 0.0000 2.25 0.255 0.0000 1.72 0.180 0.0000 1.21 0.083 0.0000 0.71 0.036 0.0000 0.14 -0.004 0.0000 -0.30 -0.024 0.0000 -0.82 -0.047 0.0000 -1.33 -0.072 0.0000 -1.84 -0.149 0.0000 -2.32 -0.224 0.0000 -2.91 -0.293 0.0000 -3.43 -0.342 0.0000 -3.91 -0.385 0.0000 -4.43 -0.420 0.0000 -4.91 -0.457 0.0000 -5.47 -0.500 0.0000 -5.95 -0.538 0.0000 Tabulated from data in file MS00281.DAT & reduced using program Q01.00L Average Reynolds #: 100700 Number of angles of attack: 97 alpha / Cl / Cm -5.95 -0.530 0.0000 -5.44 -0.493 0.0000 -5.03 -0.460 0.0000 -4.48 -0.419 0.0000 -4.13 -0.394 0.0000 -3.45 -0.347 0.0000 -3.03 -0.317 0.0000 -2.39 -0.240 0.0000 -1.99 -0.183 0.0000 -1.41 -0.090 0.0000 -0.98 -0.034 0.0000 -0.31 -0.012 0.0000 0.07 0.009 0.0000 0.62 0.049 0.0000 1.05 0.133 0.0000 1.65 0.221 0.0000 2.10 0.270 0.0000 2.62 0.321 0.0000 3.08 0.364 0.0000 3.65 0.414 0.0000 4.12 0.454 0.0000 4.63 0.497 0.0000 5.13 0.540 0.0000 5.60 0.581 0.0000 6.24 0.629 0.0000 6.67 0.661 0.0000 7.26 0.703 0.0000 7.67 0.732 0.0000 8.29 0.771 0.0000 8.73 0.795 0.0000 9.30 0.826 0.0000 9.73 0.835 0.0000 10.30 0.827 0.0000 10.77 0.836 0.0000 11.25 0.791 0.0000 11.69 0.808 0.0000 12.30 0.807 0.0000 12.75 0.743 0.0000 13.26 0.751 0.0000 13.72 0.763 0.0000 14.29 0.737 0.0000 14.71 0.762 0.0000 15.27 0.726 0.0000 15.79 0.749 0.0000 16.24 0.758 0.0000 16.79 0.758 0.0000 17.27 0.797 0.0000 17.78 0.789 0.0000 18.29 0.797 0.0000 17.76 0.801 0.0000 17.41 0.786 0.0000 16.96 0.778 0.0000 16.39 0.774 0.0000 15.97 0.728 0.0000 15.38 0.741 0.0000 14.92 0.740 0.0000 14.41 0.744 0.0000 13.91 0.751 0.0000 13.40 0.743 0.0000 12.92 0.758 0.0000 12.37 0.759 0.0000 11.94 0.791 0.0000 11.41 0.823 0.0000 11.02 0.824 0.0000 10.41 0.828 0.0000 9.94 0.844 0.0000 9.38 0.817 0.0000 8.98 0.797 0.0000 8.35 0.762 0.0000 7.83 0.728 0.0000 7.40 0.701 0.0000 6.93 0.668 0.0000 6.28 0.619 0.0000 5.78 0.581 0.0000 5.35 0.544 0.0000 4.89 0.507 0.0000 4.32 0.458 0.0000 3.81 0.416 0.0000 3.32 0.375 0.0000 2.82 0.328 0.0000 2.31 0.286 0.0000 1.80 0.232 0.0000 1.24 0.162 0.0000 0.81 0.084 0.0000 0.24 0.015 0.0000 -0.27 -0.009 0.0000 -0.78 -0.034 0.0000 -1.34 -0.089 0.0000 -1.83 -0.162 0.0000 -2.33 -0.230 0.0000 -2.87 -0.288 0.0000 -3.35 -0.328 0.0000 -3.86 -0.364 0.0000 -4.39 -0.400 0.0000 -4.90 -0.440 0.0000 -5.49 -0.486 0.0000 -6.00 -0.527 0.0000 Tabulated from data in file MS00282.DAT & reduced using program Q01.00L File n0009.lft created on 12-05-1997 at 15:25:50 using program FORMAT :::::::::::::: N6409.LFT :::::::::::::: Airfoil: NACA 6409 Builder: H. Halsey Comment: clean Number of Reynolds #'s: 3 Average Reynolds #: 61300 Number of angles of attack: 33 alpha / Cl / Cm -5.79 -0.308 -0.1630 -4.41 -0.261 -0.1630 -2.77 -0.014 -0.1630 -1.24 0.208 -0.1630 0.23 0.436 -0.1630 1.99 0.610 -0.1630 3.38 0.748 -0.1630 4.88 0.865 -0.1630 6.46 0.813 -0.1630 7.89 0.831 -0.1630 9.38 0.888 -0.1630 11.16 1.426 -0.1630 12.64 1.402 -0.1630 14.02 1.375 -0.1630 15.66 1.366 -0.1630 16.96 1.355 -0.1630 18.56 1.328 -0.1630 17.11 1.327 -0.1630 15.71 1.347 -0.1630 14.24 1.361 -0.1630 12.73 1.381 -0.1630 11.10 1.401 -0.1630 9.70 1.302 -0.1630 8.04 0.790 -0.1630 6.55 0.857 -0.1630 4.88 0.856 -0.1630 3.52 0.734 -0.1630 1.90 0.592 -0.1630 0.43 0.419 -0.1630 -1.04 0.215 -0.1630 -2.64 -0.007 -0.1630 -4.21 -0.286 -0.1630 -5.75 -0.361 -0.1630 Tabulated from data in file AB00186.DAT & reduced using program Q01.00L Average Reynolds #: 101600 Number of angles of attack: 33 alpha / Cl / Cm -5.88 -0.326 -0.1630 -4.26 -0.142 -0.1630 -2.75 0.192 -0.1630 -1.11 0.412 -0.1630 0.32 0.559 -0.1630 1.92 0.706 -0.1630 3.31 0.842 -0.1630 4.96 0.993 -0.1630 6.43 1.120 -0.1630 8.07 1.262 -0.1630 9.69 1.384 -0.1630 11.04 1.445 -0.1630 12.54 1.402 -0.1630 14.11 1.382 -0.1630 15.55 1.367 -0.1630 16.86 1.345 -0.1630 18.50 1.228 -0.1630 17.02 1.327 -0.1630 15.70 1.349 -0.1630 14.14 1.366 -0.1630 12.64 1.385 -0.1630 11.09 1.434 -0.1630 9.66 1.371 -0.1630 8.19 1.255 -0.1630 6.56 1.114 -0.1630 4.90 0.963 -0.1630 3.43 0.825 -0.1630 2.00 0.689 -0.1630 0.48 0.548 -0.1630 -1.15 0.383 -0.1630 -2.64 0.176 -0.1630 -4.28 -0.173 -0.1630 -5.70 -0.321 -0.1630 Tabulated from data in file AB00188.DAT & reduced using program Q01.00L Average Reynolds #: 202400 Number of angles of attack: 33 alpha / Cl / Cm -5.83 -0.115 -0.1630 -4.48 0.092 -0.1630 -2.86 0.285 -0.1630 -1.29 0.438 -0.1630 0.17 0.589 -0.1630 1.80 0.749 -0.1630 3.30 0.895 -0.1630 4.87 1.045 -0.1630 6.53 1.197 -0.1630 8.02 1.321 -0.1630 10.05 1.436 -0.1630 11.28 1.426 -0.1630 12.77 1.402 -0.1630 14.07 1.384 -0.1630 15.77 1.376 -0.1630 17.17 1.357 -0.1630 18.44 1.191 -0.1630 17.04 1.365 -0.1630 15.46 1.382 -0.1630 14.05 1.382 -0.1630 12.52 1.406 -0.1630 10.93 1.430 -0.1630 9.33 1.407 -0.1630 7.89 1.311 -0.1630 6.49 1.192 -0.1630 4.88 1.039 -0.1630 3.31 0.889 -0.1630 1.84 0.745 -0.1630 0.30 0.592 -0.1630 -1.12 0.448 -0.1630 -2.67 0.296 -0.1630 -4.10 0.148 -0.1630 -5.84 -0.130 -0.1630 Tabulated from data in file AB00190.DAT & reduced using program Q01.00L File n6409.lft created on 12-05-1997 at 15:25:50 using program FORMAT :::::::::::::: N64A.LFT :::::::::::::: Airfoil: NACA 64A010 Builder: B. Champine Comment: clean Number of Reynolds #'s: 9 Average Reynolds #: 22100 Number of angles of attack: 97 alpha / Cl / Cm -6.18 -0.588 0.0000 -5.65 -0.555 0.0000 -5.09 -0.436 0.0000 -4.63 -0.383 0.0000 -4.01 -0.311 0.0000 -3.60 -0.243 0.0000 -3.02 -0.103 0.0000 -2.58 -0.139 0.0000 -1.99 -0.049 0.0000 -1.52 -0.024 0.0000 -0.95 0.019 0.0000 -0.55 0.035 0.0000 0.04 0.044 0.0000 0.46 0.092 0.0000 1.09 0.103 0.0000 1.48 0.125 0.0000 2.01 0.143 0.0000 2.51 0.189 0.0000 3.11 0.245 0.0000 3.51 0.288 0.0000 4.04 0.325 0.0000 4.57 0.386 0.0000 5.15 0.563 0.0000 5.61 0.635 0.0000 6.15 0.660 0.0000 6.65 0.714 0.0000 7.14 0.729 0.0000 7.66 0.755 0.0000 8.19 0.779 0.0000 8.65 0.808 0.0000 9.27 0.836 0.0000 9.64 0.859 0.0000 10.22 0.837 0.0000 10.67 0.823 0.0000 11.18 0.798 0.0000 11.64 0.799 0.0000 12.28 0.756 0.0000 12.68 0.767 0.0000 13.17 0.748 0.0000 13.68 0.775 0.0000 14.18 0.763 0.0000 14.66 0.783 0.0000 15.22 0.842 0.0000 15.68 0.852 0.0000 16.27 0.826 0.0000 16.65 0.884 0.0000 17.31 0.931 0.0000 17.70 0.914 0.0000 18.26 0.989 0.0000 17.82 0.921 0.0000 17.27 0.928 0.0000 16.76 0.847 0.0000 16.29 0.884 0.0000 15.75 0.804 0.0000 15.28 0.835 0.0000 14.78 0.791 0.0000 14.25 0.809 0.0000 13.77 0.811 0.0000 13.22 0.783 0.0000 12.75 0.814 0.0000 12.25 0.817 0.0000 11.77 0.770 0.0000 11.28 0.891 0.0000 10.79 0.906 0.0000 10.31 0.913 0.0000 9.77 0.920 0.0000 9.33 0.903 0.0000 8.81 0.880 0.0000 8.30 0.855 0.0000 7.79 0.837 0.0000 7.30 0.800 0.0000 6.74 0.770 0.0000 6.29 0.738 0.0000 5.70 0.663 0.0000 5.24 0.590 0.0000 4.69 0.443 0.0000 4.13 0.377 0.0000 3.64 0.328 0.0000 3.08 0.285 0.0000 2.62 0.235 0.0000 2.11 0.212 0.0000 1.62 0.176 0.0000 1.07 0.168 0.0000 0.60 0.146 0.0000 0.14 0.138 0.0000 -0.40 0.107 0.0000 -0.91 0.090 0.0000 -1.44 0.037 0.0000 -1.95 0.017 0.0000 -2.44 -0.026 0.0000 -2.98 -0.059 0.0000 -3.48 -0.110 0.0000 -3.94 -0.173 0.0000 -4.50 -0.274 0.0000 -5.01 -0.349 0.0000 -5.59 -0.433 0.0000 -6.10 -0.483 0.0000 Tabulated from data in file MS00242.DAT & reduced using program Q01.00L Average Reynolds #: 30600 Number of angles of attack: 97 alpha / Cl / Cm -6.73 -0.591 0.0000 -5.70 -0.568 0.0000 -5.17 -0.551 0.0000 -4.67 -0.501 0.0000 -4.20 -0.421 0.0000 -3.61 -0.269 0.0000 -3.16 -0.192 0.0000 -2.54 -0.138 0.0000 -2.10 -0.096 0.0000 -1.59 -0.057 0.0000 -1.06 -0.027 0.0000 -0.52 -0.012 0.0000 -0.09 -0.004 0.0000 0.50 0.017 0.0000 0.94 0.022 0.0000 1.54 0.058 0.0000 1.95 0.082 0.0000 2.49 0.139 0.0000 2.94 0.166 0.0000 3.54 0.237 0.0000 4.08 0.356 0.0000 4.60 0.488 0.0000 5.00 0.523 0.0000 5.66 0.572 0.0000 6.05 0.584 0.0000 6.65 0.615 0.0000 7.01 0.651 0.0000 7.69 0.685 0.0000 8.07 0.713 0.0000 8.72 0.755 0.0000 9.16 0.770 0.0000 9.73 0.800 0.0000 10.07 0.840 0.0000 10.64 0.840 0.0000 11.08 0.858 0.0000 11.62 0.771 0.0000 12.13 0.761 0.0000 12.75 0.761 0.0000 13.07 0.694 0.0000 13.68 0.652 0.0000 14.03 0.666 0.0000 14.65 0.677 0.0000 15.10 0.652 0.0000 15.64 0.652 0.0000 16.12 0.673 0.0000 16.66 0.672 0.0000 17.04 0.728 0.0000 17.70 0.733 0.0000 18.16 0.743 0.0000 17.79 0.750 0.0000 17.36 0.725 0.0000 16.79 0.716 0.0000 16.39 0.688 0.0000 15.74 0.660 0.0000 15.36 0.668 0.0000 14.80 0.651 0.0000 14.36 0.650 0.0000 13.73 0.663 0.0000 13.35 0.654 0.0000 12.78 0.661 0.0000 12.35 0.710 0.0000 11.80 0.699 0.0000 11.36 0.735 0.0000 10.82 0.774 0.0000 10.34 0.767 0.0000 9.78 0.774 0.0000 9.36 0.767 0.0000 8.82 0.743 0.0000 8.38 0.707 0.0000 7.80 0.673 0.0000 7.40 0.635 0.0000 6.75 0.613 0.0000 6.38 0.594 0.0000 5.73 0.565 0.0000 5.33 0.531 0.0000 4.70 0.469 0.0000 4.26 0.395 0.0000 3.64 0.277 0.0000 3.29 0.218 0.0000 2.56 0.154 0.0000 2.10 0.115 0.0000 1.62 0.075 0.0000 1.20 0.047 0.0000 0.61 0.025 0.0000 0.21 0.018 0.0000 -0.41 0.015 0.0000 -0.86 -0.004 0.0000 -1.39 -0.026 0.0000 -1.78 -0.051 0.0000 -2.45 -0.100 0.0000 -2.86 -0.132 0.0000 -3.46 -0.200 0.0000 -3.91 -0.293 0.0000 -4.49 -0.405 0.0000 -4.95 -0.469 0.0000 -5.55 -0.514 0.0000 -5.96 -0.539 0.0000 Tabulated from data in file MS00265.DAT & reduced using program Q01.00L Average Reynolds #: 40600 Number of angles of attack: 97 alpha / Cl / Cm -5.97 -0.515 0.0000 -5.64 -0.500 0.0000 -5.05 -0.470 0.0000 -4.65 -0.456 0.0000 -4.07 -0.411 0.0000 -3.62 -0.343 0.0000 -3.06 -0.213 0.0000 -2.54 -0.137 0.0000 -1.99 -0.068 0.0000 -1.49 -0.025 0.0000 -1.03 0.002 0.0000 -0.49 0.014 0.0000 -0.06 0.026 0.0000 0.52 0.049 0.0000 1.05 0.071 0.0000 1.51 0.092 0.0000 2.00 0.125 0.0000 2.53 0.177 0.0000 3.15 0.284 0.0000 3.53 0.367 0.0000 4.08 0.467 0.0000 4.60 0.533 0.0000 5.14 0.560 0.0000 5.65 0.590 0.0000 6.14 0.618 0.0000 6.66 0.647 0.0000 7.14 0.682 0.0000 7.68 0.712 0.0000 8.23 0.751 0.0000 8.68 0.775 0.0000 9.07 0.801 0.0000 9.76 0.841 0.0000 10.20 0.859 0.0000 10.74 0.820 0.0000 11.24 0.869 0.0000 11.76 0.798 0.0000 12.17 0.793 0.0000 12.69 0.772 0.0000 13.28 0.733 0.0000 13.68 0.718 0.0000 14.14 0.714 0.0000 14.68 0.718 0.0000 15.09 0.710 0.0000 15.65 0.699 0.0000 16.25 0.738 0.0000 16.68 0.789 0.0000 17.17 0.788 0.0000 17.72 0.804 0.0000 18.26 0.866 0.0000 17.71 0.790 0.0000 17.26 0.741 0.0000 16.81 0.755 0.0000 16.22 0.756 0.0000 15.74 0.708 0.0000 15.27 0.727 0.0000 14.78 0.697 0.0000 14.38 0.691 0.0000 13.83 0.694 0.0000 13.28 0.737 0.0000 12.83 0.729 0.0000 12.39 0.777 0.0000 11.84 0.811 0.0000 11.30 0.799 0.0000 10.86 0.819 0.0000 10.27 0.801 0.0000 9.81 0.824 0.0000 9.25 0.801 0.0000 8.82 0.776 0.0000 8.29 0.751 0.0000 7.84 0.726 0.0000 7.39 0.695 0.0000 6.77 0.660 0.0000 6.41 0.645 0.0000 5.76 0.613 0.0000 5.25 0.593 0.0000 4.76 0.561 0.0000 4.21 0.505 0.0000 3.71 0.421 0.0000 3.19 0.322 0.0000 2.64 0.244 0.0000 2.10 0.179 0.0000 1.56 0.132 0.0000 1.13 0.100 0.0000 0.62 0.087 0.0000 0.12 0.072 0.0000 -0.33 0.050 0.0000 -0.78 0.025 0.0000 -1.40 -0.004 0.0000 -1.93 -0.033 0.0000 -2.43 -0.097 0.0000 -3.00 -0.180 0.0000 -3.44 -0.264 0.0000 -4.01 -0.377 0.0000 -4.50 -0.427 0.0000 -5.03 -0.468 0.0000 -5.58 -0.499 0.0000 -6.04 -0.522 0.0000 Tabulated from data in file MS00266.DAT & reduced using program Q01.00L Average Reynolds #: 50600 Number of angles of attack: 97 alpha / Cl / Cm -6.24 -0.545 0.0000 -5.65 -0.522 0.0000 -5.23 -0.506 0.0000 -4.62 -0.471 0.0000 -4.23 -0.446 0.0000 -3.67 -0.398 0.0000 -3.18 -0.340 0.0000 -2.57 -0.244 0.0000 -2.12 -0.147 0.0000 -1.50 -0.050 0.0000 -1.01 -0.006 0.0000 -0.49 0.009 0.0000 -0.10 0.020 0.0000 0.55 0.039 0.0000 1.08 0.053 0.0000 1.49 0.082 0.0000 1.96 0.126 0.0000 2.52 0.214 0.0000 2.92 0.304 0.0000 3.57 0.420 0.0000 4.05 0.469 0.0000 4.60 0.512 0.0000 5.07 0.536 0.0000 5.62 0.571 0.0000 6.08 0.591 0.0000 6.68 0.623 0.0000 7.05 0.649 0.0000 7.73 0.695 0.0000 8.08 0.716 0.0000 8.73 0.745 0.0000 9.17 0.773 0.0000 9.71 0.799 0.0000 10.10 0.817 0.0000 10.68 0.838 0.0000 11.16 0.844 0.0000 11.70 0.816 0.0000 12.18 0.851 0.0000 12.72 0.818 0.0000 13.13 0.776 0.0000 13.71 0.780 0.0000 14.05 0.740 0.0000 14.69 0.740 0.0000 15.18 0.782 0.0000 15.72 0.762 0.0000 16.14 0.755 0.0000 16.72 0.803 0.0000 17.09 0.790 0.0000 17.62 0.826 0.0000 18.14 0.852 0.0000 17.81 0.845 0.0000 17.39 0.809 0.0000 16.81 0.805 0.0000 16.45 0.817 0.0000 15.83 0.772 0.0000 15.40 0.731 0.0000 14.80 0.731 0.0000 14.38 0.730 0.0000 13.76 0.733 0.0000 13.40 0.775 0.0000 12.81 0.780 0.0000 12.43 0.810 0.0000 11.79 0.827 0.0000 11.42 0.840 0.0000 10.78 0.844 0.0000 10.25 0.817 0.0000 9.80 0.809 0.0000 9.40 0.787 0.0000 8.79 0.768 0.0000 8.42 0.749 0.0000 7.75 0.711 0.0000 7.37 0.680 0.0000 6.74 0.639 0.0000 6.35 0.613 0.0000 5.72 0.584 0.0000 5.32 0.565 0.0000 4.72 0.536 0.0000 4.30 0.507 0.0000 3.69 0.451 0.0000 3.33 0.404 0.0000 2.68 0.276 0.0000 2.23 0.178 0.0000 1.60 0.104 0.0000 1.23 0.088 0.0000 0.61 0.063 0.0000 0.20 0.044 0.0000 -0.40 0.034 0.0000 -0.87 0.024 0.0000 -1.40 -0.010 0.0000 -1.92 -0.090 0.0000 -2.44 -0.165 0.0000 -2.87 -0.252 0.0000 -3.52 -0.363 0.0000 -3.91 -0.403 0.0000 -4.49 -0.439 0.0000 -4.95 -0.476 0.0000 -5.55 -0.505 0.0000 -5.91 -0.526 0.0000 Tabulated from data in file MS00267.DAT & reduced using program Q01.00L Average Reynolds #: 60900 Number of angles of attack: 97 alpha / Cl / Cm -5.98 -0.539 0.0000 -5.71 -0.527 0.0000 -5.10 -0.498 0.0000 -4.69 -0.477 0.0000 -4.20 -0.440 0.0000 -3.66 -0.391 0.0000 -3.20 -0.361 0.0000 -2.64 -0.314 0.0000 -2.12 -0.229 0.0000 -1.58 -0.123 0.0000 -1.06 -0.025 0.0000 -0.54 0.012 0.0000 -0.08 0.013 0.0000 0.48 0.041 0.0000 0.92 0.059 0.0000 1.48 0.079 0.0000 1.99 0.170 0.0000 2.50 0.287 0.0000 3.11 0.375 0.0000 3.52 0.406 0.0000 4.07 0.462 0.0000 4.54 0.478 0.0000 5.04 0.530 0.0000 5.61 0.566 0.0000 6.07 0.595 0.0000 6.58 0.629 0.0000 7.11 0.664 0.0000 7.66 0.699 0.0000 8.12 0.726 0.0000 8.68 0.754 0.0000 9.08 0.773 0.0000 9.66 0.808 0.0000 10.12 0.825 0.0000 10.72 0.846 0.0000 11.14 0.849 0.0000 11.69 0.855 0.0000 12.15 0.840 0.0000 12.71 0.859 0.0000 13.16 0.811 0.0000 13.65 0.786 0.0000 14.20 0.748 0.0000 14.67 0.752 0.0000 15.19 0.739 0.0000 15.65 0.732 0.0000 16.17 0.740 0.0000 16.67 0.754 0.0000 17.21 0.770 0.0000 17.61 0.803 0.0000 18.18 0.814 0.0000 17.78 0.818 0.0000 17.31 0.783 0.0000 16.75 0.759 0.0000 16.31 0.752 0.0000 15.78 0.750 0.0000 15.35 0.741 0.0000 14.77 0.741 0.0000 14.39 0.781 0.0000 13.77 0.794 0.0000 13.37 0.822 0.0000 12.82 0.838 0.0000 12.37 0.853 0.0000 11.81 0.854 0.0000 11.34 0.844 0.0000 10.78 0.839 0.0000 10.37 0.829 0.0000 9.76 0.805 0.0000 9.38 0.791 0.0000 8.78 0.762 0.0000 8.33 0.738 0.0000 7.73 0.704 0.0000 7.33 0.678 0.0000 6.74 0.638 0.0000 6.37 0.613 0.0000 5.75 0.574 0.0000 5.29 0.545 0.0000 4.74 0.509 0.0000 4.30 0.477 0.0000 3.68 0.431 0.0000 3.27 0.402 0.0000 2.65 0.314 0.0000 2.22 0.224 0.0000 1.58 0.094 0.0000 1.19 0.051 0.0000 0.61 0.035 0.0000 0.16 0.020 0.0000 -0.43 0.027 0.0000 -0.76 0.017 0.0000 -1.45 -0.089 0.0000 -1.90 -0.166 0.0000 -2.50 -0.289 0.0000 -2.94 -0.342 0.0000 -3.51 -0.384 0.0000 -3.96 -0.407 0.0000 -4.55 -0.456 0.0000 -4.98 -0.488 0.0000 -5.59 -0.516 0.0000 -5.94 -0.538 0.0000 Tabulated from data in file MS00268.DAT & reduced using program Q01.00L Average Reynolds #: 80800 Number of angles of attack: 97 alpha / Cl / Cm -5.90 -0.551 0.0000 -5.73 -0.541 0.0000 -5.16 -0.511 0.0000 -4.60 -0.484 0.0000 -4.12 -0.442 0.0000 -3.64 -0.408 0.0000 -3.13 -0.375 0.0000 -2.55 -0.324 0.0000 -2.02 -0.253 0.0000 -1.55 -0.179 0.0000 -1.04 -0.097 0.0000 -0.51 -0.016 0.0000 0.06 0.018 0.0000 0.47 0.021 0.0000 0.96 0.039 0.0000 1.49 0.128 0.0000 2.09 0.245 0.0000 2.54 0.323 0.0000 3.14 0.377 0.0000 3.58 0.411 0.0000 4.08 0.450 0.0000 4.59 0.491 0.0000 5.15 0.525 0.0000 5.64 0.556 0.0000 6.08 0.587 0.0000 6.62 0.624 0.0000 7.15 0.662 0.0000 7.69 0.696 0.0000 8.20 0.728 0.0000 8.72 0.760 0.0000 9.21 0.790 0.0000 9.73 0.799 0.0000 10.19 0.809 0.0000 10.70 0.830 0.0000 11.20 0.812 0.0000 11.72 0.793 0.0000 12.18 0.808 0.0000 12.70 0.812 0.0000 13.24 0.812 0.0000 13.67 0.768 0.0000 14.25 0.771 0.0000 14.68 0.793 0.0000 15.25 0.716 0.0000 15.64 0.706 0.0000 16.10 0.728 0.0000 16.68 0.747 0.0000 17.17 0.739 0.0000 17.65 0.792 0.0000 18.20 0.780 0.0000 17.71 0.747 0.0000 17.29 0.764 0.0000 16.82 0.743 0.0000 16.26 0.734 0.0000 15.83 0.726 0.0000 15.24 0.721 0.0000 14.85 0.762 0.0000 14.29 0.772 0.0000 13.80 0.791 0.0000 13.31 0.792 0.0000 12.81 0.792 0.0000 12.24 0.774 0.0000 11.85 0.793 0.0000 11.29 0.805 0.0000 10.83 0.808 0.0000 10.42 0.802 0.0000 9.83 0.793 0.0000 9.38 0.774 0.0000 8.81 0.746 0.0000 8.29 0.716 0.0000 7.82 0.688 0.0000 7.21 0.647 0.0000 6.72 0.614 0.0000 6.32 0.585 0.0000 5.76 0.545 0.0000 5.24 0.512 0.0000 4.74 0.483 0.0000 4.30 0.447 0.0000 3.69 0.400 0.0000 3.20 0.367 0.0000 2.73 0.320 0.0000 2.29 0.255 0.0000 1.64 0.143 0.0000 1.10 0.038 0.0000 0.61 0.001 0.0000 0.05 0.000 0.0000 -0.46 -0.029 0.0000 -0.95 -0.099 0.0000 -1.45 -0.176 0.0000 -2.00 -0.268 0.0000 -2.55 -0.341 0.0000 -2.99 -0.381 0.0000 -3.49 -0.418 0.0000 -3.88 -0.447 0.0000 -4.53 -0.491 0.0000 -5.06 -0.523 0.0000 -5.51 -0.548 0.0000 -6.15 -0.590 0.0000 Tabulated from data in file MS00269.DAT & reduced using program Q01.00L Average Reynolds #: 101000 Number of angles of attack: 97 alpha / Cl / Cm -6.25 -0.584 0.0000 -5.68 -0.544 0.0000 -5.21 -0.518 0.0000 -4.62 -0.484 0.0000 -4.15 -0.455 0.0000 -3.65 -0.413 0.0000 -3.08 -0.370 0.0000 -2.66 -0.341 0.0000 -2.14 -0.300 0.0000 -1.59 -0.243 0.0000 -1.07 -0.164 0.0000 -0.54 -0.082 0.0000 -0.05 -0.002 0.0000 0.46 0.010 0.0000 0.95 0.092 0.0000 1.46 0.184 0.0000 2.04 0.283 0.0000 2.53 0.336 0.0000 3.11 0.380 0.0000 3.54 0.411 0.0000 4.06 0.452 0.0000 4.53 0.481 0.0000 5.04 0.512 0.0000 5.59 0.549 0.0000 6.04 0.581 0.0000 6.60 0.622 0.0000 7.06 0.655 0.0000 7.63 0.693 0.0000 8.15 0.726 0.0000 8.64 0.759 0.0000 9.14 0.791 0.0000 9.67 0.801 0.0000 10.15 0.793 0.0000 10.64 0.798 0.0000 11.11 0.808 0.0000 11.69 0.804 0.0000 12.16 0.785 0.0000 12.66 0.816 0.0000 13.11 0.777 0.0000 13.71 0.783 0.0000 14.20 0.778 0.0000 14.63 0.762 0.0000 15.19 0.717 0.0000 15.60 0.705 0.0000 16.14 0.738 0.0000 16.67 0.747 0.0000 17.18 0.773 0.0000 17.71 0.741 0.0000 18.13 0.745 0.0000 17.81 0.743 0.0000 17.35 0.769 0.0000 16.74 0.725 0.0000 16.37 0.728 0.0000 15.78 0.727 0.0000 15.31 0.724 0.0000 14.78 0.780 0.0000 14.34 0.779 0.0000 13.81 0.785 0.0000 13.31 0.783 0.0000 12.79 0.799 0.0000 12.35 0.785 0.0000 11.77 0.788 0.0000 11.37 0.814 0.0000 10.79 0.828 0.0000 10.37 0.807 0.0000 9.79 0.806 0.0000 9.36 0.787 0.0000 8.81 0.763 0.0000 8.32 0.730 0.0000 7.76 0.692 0.0000 7.34 0.663 0.0000 6.76 0.623 0.0000 6.32 0.591 0.0000 5.67 0.544 0.0000 5.30 0.517 0.0000 4.67 0.478 0.0000 4.27 0.458 0.0000 3.69 0.410 0.0000 3.21 0.373 0.0000 2.66 0.333 0.0000 2.27 0.298 0.0000 1.61 0.205 0.0000 1.18 0.122 0.0000 0.58 0.019 0.0000 0.19 -0.020 0.0000 -0.46 -0.076 0.0000 -0.89 -0.142 0.0000 -1.50 -0.236 0.0000 -1.87 -0.282 0.0000 -2.49 -0.334 0.0000 -2.95 -0.369 0.0000 -3.51 -0.407 0.0000 -4.01 -0.447 0.0000 -4.54 -0.481 0.0000 -4.97 -0.506 0.0000 -5.55 -0.541 0.0000 -6.08 -0.576 0.0000 Tabulated from data in file MS00270.DAT & reduced using program Q01.00L Average Reynolds #: 204000 Number of angles of attack: 33 alpha / Cl / Cm -6.03 -0.568 0.0000 -4.45 -0.459 0.0000 -2.69 -0.317 0.0000 -1.16 -0.146 0.0000 0.15 0.018 0.0000 1.63 0.183 0.0000 3.38 0.389 0.0000 4.68 0.486 0.0000 6.12 0.595 0.0000 7.70 0.713 0.0000 9.21 0.817 0.0000 10.77 0.857 0.0000 12.42 0.821 0.0000 13.78 0.778 0.0000 15.23 0.699 0.0000 16.94 0.712 0.0000 18.42 0.789 0.0000 16.62 0.717 0.0000 14.98 0.698 0.0000 13.66 0.808 0.0000 12.18 0.837 0.0000 10.70 0.859 0.0000 9.28 0.821 0.0000 7.68 0.704 0.0000 6.15 0.593 0.0000 4.61 0.473 0.0000 3.03 0.351 0.0000 1.52 0.162 0.0000 -0.01 -0.009 0.0000 -1.55 -0.210 0.0000 -3.43 -0.394 0.0000 -4.93 -0.504 0.0000 -6.28 -0.598 0.0000 Tabulated from data in file AB00247.DAT & reduced using program Q01.00L Average Reynolds #: 305400 Number of angles of attack: 33 alpha / Cl / Cm -6.25 -0.597 0.0000 -4.41 -0.460 0.0000 -2.65 -0.300 0.0000 -1.01 -0.094 0.0000 0.33 0.030 0.0000 1.66 0.157 0.0000 3.23 0.357 0.0000 4.62 0.479 0.0000 6.14 0.601 0.0000 7.72 0.717 0.0000 9.22 0.819 0.0000 10.78 0.868 0.0000 12.25 0.858 0.0000 13.80 0.786 0.0000 15.34 0.712 0.0000 17.00 0.738 0.0000 18.45 0.840 0.0000 16.49 0.720 0.0000 15.03 0.704 0.0000 13.73 0.826 0.0000 12.26 0.858 0.0000 10.77 0.860 0.0000 9.18 0.816 0.0000 7.65 0.706 0.0000 6.13 0.592 0.0000 4.65 0.475 0.0000 3.13 0.338 0.0000 1.57 0.142 0.0000 -0.15 -0.017 0.0000 -1.66 -0.179 0.0000 -3.58 -0.407 0.0000 -5.00 -0.511 0.0000 -6.32 -0.609 0.0000 Tabulated from data in file AB00249.DAT & reduced using program Q01.00L File n64a.lft created on 12-05-1997 at 15:25:50 using program FORMAT :::::::::::::: R140A.LFT :::::::::::::: Airfoil: R140 (A) Builder: W. Friedlander Comment: clean Number of Reynolds #'s: 3 Average Reynolds #: 102300 Number of angles of attack: 33 alpha / Cl / Cm -5.74 -0.518 -0.0120 -4.08 -0.449 -0.0120 -2.56 -0.372 -0.0120 -0.95 -0.079 -0.0120 0.50 0.162 -0.0120 2.17 0.393 -0.0120 3.61 0.488 -0.0120 5.04 0.578 -0.0120 6.60 0.638 -0.0120 8.23 0.718 -0.0120 9.55 0.779 -0.0120 11.22 0.851 -0.0120 12.57 0.850 -0.0120 14.12 0.812 -0.0120 15.63 0.740 -0.0120 17.18 0.716 -0.0120 18.55 0.728 -0.0120 16.89 0.713 -0.0120 15.51 0.730 -0.0120 13.98 0.817 -0.0120 12.54 0.855 -0.0120 10.97 0.837 -0.0120 9.53 0.766 -0.0120 7.89 0.686 -0.0120 6.50 0.619 -0.0120 4.94 0.556 -0.0120 3.42 0.462 -0.0120 1.73 0.326 -0.0120 0.33 0.105 -0.0120 -1.32 -0.170 -0.0120 -2.77 -0.390 -0.0120 -4.36 -0.454 -0.0120 -5.85 -0.522 -0.0120 Tabulated from data in file AB00202.DAT & reduced using program Q01.00L Average Reynolds #: 204200 Number of angles of attack: 33 alpha / Cl / Cm -5.73 -0.527 -0.0120 -4.13 -0.408 -0.0120 -2.68 -0.250 -0.0120 -0.93 -0.076 -0.0120 0.34 0.027 -0.0120 1.99 0.206 -0.0120 3.48 0.411 -0.0120 5.09 0.552 -0.0120 6.50 0.619 -0.0120 7.99 0.693 -0.0120 9.56 0.785 -0.0120 11.17 0.853 -0.0120 12.61 0.862 -0.0120 14.10 0.822 -0.0120 15.84 0.730 -0.0120 17.12 0.694 -0.0120 18.75 0.715 -0.0120 16.80 0.720 -0.0120 15.33 0.771 -0.0120 13.77 0.834 -0.0120 12.54 0.861 -0.0120 11.10 0.857 -0.0120 9.51 0.778 -0.0120 7.99 0.686 -0.0120 6.48 0.612 -0.0120 4.83 0.535 -0.0120 3.45 0.398 -0.0120 1.89 0.182 -0.0120 0.32 0.015 -0.0120 -1.23 -0.112 -0.0120 -2.75 -0.264 -0.0120 -4.33 -0.442 -0.0120 -5.93 -0.544 -0.0120 Tabulated from data in file AB00204.DAT & reduced using program Q01.00L Average Reynolds #: 306000 Number of angles of attack: 33 alpha / Cl / Cm -5.69 -0.528 -0.0120 -3.92 -0.344 -0.0120 -2.63 -0.228 -0.0120 -0.86 -0.078 -0.0120 0.54 0.040 -0.0120 2.08 0.195 -0.0120 3.43 0.360 -0.0120 5.05 0.547 -0.0120 6.49 0.626 -0.0120 7.99 0.699 -0.0120 9.59 0.807 -0.0120 11.10 0.868 -0.0120 12.45 0.886 -0.0120 14.22 0.819 -0.0120 15.91 0.736 -0.0120 17.41 0.714 -0.0120 18.48 0.746 -0.0120 16.80 0.707 -0.0120 15.27 0.770 -0.0120 13.87 0.855 -0.0120 12.61 0.873 -0.0120 11.08 0.869 -0.0120 9.47 0.797 -0.0120 8.00 0.697 -0.0120 6.43 0.619 -0.0120 4.91 0.530 -0.0120 3.39 0.349 -0.0120 1.88 0.167 -0.0120 0.34 0.017 -0.0120 -1.24 -0.118 -0.0120 -2.89 -0.253 -0.0120 -4.49 -0.413 -0.0120 -6.08 -0.561 -0.0120 Tabulated from data in file AB00206.DAT & reduced using program Q01.00L File r140a.lft created on 12-05-1997 at 15:25:50 using program FORMAT :::::::::::::: RG15B.LFT :::::::::::::: Airfoil: RG15 (B) Builder: B. Champine Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 61400 Number of angles of attack: 33 alpha / Cl / Cm -6.95 -0.442 -0.0580 -4.99 -0.299 -0.0580 -3.50 -0.183 -0.0580 -1.89 -0.069 -0.0580 -0.34 0.086 -0.0580 1.11 0.246 -0.0580 2.83 0.521 -0.0580 4.22 0.664 -0.0580 5.71 0.783 -0.0580 7.38 0.901 -0.0580 8.90 0.990 -0.0580 10.26 1.043 -0.0580 11.89 1.036 -0.0580 13.37 1.053 -0.0580 14.75 1.057 -0.0580 16.27 1.006 -0.0580 17.75 0.990 -0.0580 16.35 1.012 -0.0580 14.97 1.012 -0.0580 13.49 1.067 -0.0580 11.89 1.065 -0.0580 10.38 1.037 -0.0580 8.87 0.976 -0.0580 7.44 0.890 -0.0580 5.84 0.784 -0.0580 4.34 0.660 -0.0580 2.79 0.515 -0.0580 1.29 0.252 -0.0580 -0.22 0.091 -0.0580 -1.89 -0.075 -0.0580 -3.36 -0.182 -0.0580 -4.92 -0.295 -0.0580 -6.50 -0.415 -0.0580 Tabulated from data in file MS00306.DAT & reduced using program Q01.00L Average Reynolds #: 101900 Number of angles of attack: 33 alpha / Cl / Cm -6.53 -0.419 -0.0580 -4.99 -0.301 -0.0580 -3.40 -0.172 -0.0580 -2.02 -0.060 -0.0580 -0.36 0.093 -0.0580 1.06 0.323 -0.0580 2.62 0.520 -0.0580 4.12 0.649 -0.0580 5.77 0.797 -0.0580 7.31 0.911 -0.0580 8.82 0.997 -0.0580 10.38 1.060 -0.0580 11.84 1.067 -0.0580 13.34 0.984 -0.0580 14.83 0.964 -0.0580 16.16 0.951 -0.0580 17.83 0.893 -0.0580 16.43 0.947 -0.0580 14.91 0.957 -0.0580 13.41 0.961 -0.0580 11.92 1.044 -0.0580 10.29 1.046 -0.0580 8.88 0.987 -0.0580 7.39 0.901 -0.0580 5.80 0.784 -0.0580 4.16 0.638 -0.0580 2.70 0.510 -0.0580 1.18 0.324 -0.0580 -0.38 0.069 -0.0580 -1.89 -0.076 -0.0580 -3.50 -0.191 -0.0580 -4.91 -0.306 -0.0580 -6.45 -0.425 -0.0580 Tabulated from data in file MS00307.DAT & reduced using program Q01.00L Average Reynolds #: 152700 Number of angles of attack: 49 alpha / Cl / Cm -6.26 -0.430 -0.0580 -5.22 -0.345 -0.0580 -4.22 -0.264 -0.0580 -3.30 -0.185 -0.0580 -2.10 -0.087 -0.0580 -1.23 -0.010 -0.0580 -0.01 0.163 -0.0580 0.96 0.312 -0.0580 1.97 0.415 -0.0580 2.83 0.499 -0.0580 3.99 0.615 -0.0580 5.04 0.712 -0.0580 5.89 0.786 -0.0580 7.08 0.884 -0.0580 8.13 0.951 -0.0580 8.92 0.996 -0.0580 9.96 1.042 -0.0580 10.94 1.069 -0.0580 12.12 1.073 -0.0580 12.96 1.037 -0.0580 14.13 0.992 -0.0580 15.22 0.998 -0.0580 16.20 0.950 -0.0580 17.21 0.920 -0.0580 18.08 0.892 -0.0580 16.71 0.925 -0.0580 15.73 0.932 -0.0580 14.70 0.965 -0.0580 13.51 1.002 -0.0580 12.68 1.045 -0.0580 11.66 1.066 -0.0580 10.76 1.064 -0.0580 9.80 1.033 -0.0580 8.82 0.986 -0.0580 7.82 0.928 -0.0580 6.76 0.854 -0.0580 5.70 0.763 -0.0580 4.63 0.669 -0.0580 3.74 0.582 -0.0580 2.61 0.470 -0.0580 1.62 0.375 -0.0580 0.58 0.256 -0.0580 -0.51 0.084 -0.0580 -1.48 -0.044 -0.0580 -2.59 -0.132 -0.0580 -3.50 -0.210 -0.0580 -4.62 -0.305 -0.0580 -5.74 -0.396 -0.0580 -6.73 -0.481 -0.0580 Tabulated from data in file AB00549.DAT & reduced using program Q01.00L Average Reynolds #: 203500 Number of angles of attack: 33 alpha / Cl / Cm -6.53 -0.435 -0.0580 -5.10 -0.321 -0.0580 -3.52 -0.184 -0.0580 -1.97 -0.033 -0.0580 -0.46 0.160 -0.0580 1.15 0.339 -0.0580 2.70 0.492 -0.0580 4.22 0.637 -0.0580 5.74 0.773 -0.0580 7.26 0.891 -0.0580 8.77 0.982 -0.0580 10.32 1.045 -0.0580 11.84 1.060 -0.0580 13.15 1.023 -0.0580 14.72 0.948 -0.0580 16.22 0.934 -0.0580 17.77 0.921 -0.0580 16.41 0.936 -0.0580 14.83 0.942 -0.0580 13.38 1.008 -0.0580 11.98 1.081 -0.0580 10.40 1.046 -0.0580 8.87 0.985 -0.0580 7.33 0.890 -0.0580 5.80 0.770 -0.0580 4.36 0.643 -0.0580 2.81 0.491 -0.0580 1.22 0.332 -0.0580 -0.39 0.153 -0.0580 -1.90 -0.036 -0.0580 -3.45 -0.187 -0.0580 -4.90 -0.312 -0.0580 -6.52 -0.440 -0.0580 Tabulated from data in file JG00080.DAT & reduced using program Q01.00L Average Reynolds #: 304700 Number of angles of attack: 33 alpha / Cl / Cm -6.50 -0.444 -0.0580 -5.18 -0.340 -0.0580 -3.65 -0.197 -0.0580 -2.14 -0.012 -0.0580 -0.54 0.162 -0.0580 0.94 0.318 -0.0580 2.54 0.493 -0.0580 4.05 0.649 -0.0580 5.64 0.795 -0.0580 7.19 0.924 -0.0580 8.78 1.032 -0.0580 10.34 1.104 -0.0580 11.63 1.131 -0.0580 13.11 1.111 -0.0580 14.66 1.035 -0.0580 16.09 0.982 -0.0580 17.68 0.943 -0.0580 16.39 0.980 -0.0580 14.88 1.020 -0.0580 13.50 1.104 -0.0580 12.01 1.139 -0.0580 10.39 1.102 -0.0580 8.95 1.037 -0.0580 7.43 0.938 -0.0580 5.85 0.810 -0.0580 4.45 0.681 -0.0580 2.83 0.515 -0.0580 1.33 0.352 -0.0580 -0.22 0.182 -0.0580 -1.71 0.033 -0.0580 -3.34 -0.172 -0.0580 -4.84 -0.319 -0.0580 -6.48 -0.452 -0.0580 Tabulated from data in file JG00078.DAT & reduced using program Q01.00L File rg15b.lft created on 12-05-1997 at 15:25:50 using program FORMAT :::::::::::::: S1210.LFT :::::::::::::: Airfoil: S1210 Builder: M. Allen Comment: clean Number of Reynolds #'s: 8 Average Reynolds #: 61100 Number of angles of attack: 53 alpha / Cl / Cm -6.22 -0.273 -0.2500 -5.15 -0.168 -0.2500 -4.15 0.183 -0.2500 -2.97 0.369 -0.2500 -1.98 0.504 -0.2500 -0.96 0.614 -0.2500 0.04 0.742 -0.2500 1.01 0.830 -0.2500 2.18 0.950 -0.2500 3.09 0.968 -0.2500 4.25 0.914 -0.2500 5.16 0.910 -0.2500 6.11 0.954 -0.2500 7.10 0.946 -0.2500 8.05 0.984 -0.2500 8.98 1.019 -0.2500 10.24 1.056 -0.2500 11.14 1.085 -0.2500 12.08 1.121 -0.2500 13.27 1.122 -0.2500 14.28 1.154 -0.2500 15.35 1.193 -0.2500 16.37 1.194 -0.2500 17.15 1.225 -0.2500 18.17 1.272 -0.2500 19.24 1.284 -0.2500 20.33 1.289 -0.2500 19.00 1.291 -0.2500 18.19 1.228 -0.2500 17.16 1.275 -0.2500 16.03 1.203 -0.2500 14.92 1.163 -0.2500 14.10 1.092 -0.2500 13.08 1.108 -0.2500 12.06 1.064 -0.2500 10.94 1.097 -0.2500 10.17 1.054 -0.2500 8.99 0.998 -0.2500 8.04 0.972 -0.2500 7.11 0.941 -0.2500 6.13 0.927 -0.2500 5.09 0.894 -0.2500 4.06 0.862 -0.2500 3.10 0.926 -0.2500 2.14 0.919 -0.2500 1.10 0.840 -0.2500 -0.12 0.692 -0.2500 -1.07 0.577 -0.2500 -1.97 0.503 -0.2500 -3.11 0.346 -0.2500 -4.27 0.192 -0.2500 -5.14 -0.182 -0.2500 -6.28 -0.246 -0.2500 Tabulated from data in file JG00127.DAT & reduced using program Q01.00L Average Reynolds #: 81200 Number of angles of attack: 53 alpha / Cl / Cm -6.42 -0.301 -0.2500 -5.22 -0.249 -0.2500 -4.04 0.194 -0.2500 -3.00 0.364 -0.2500 -1.94 0.560 -0.2500 -0.71 0.705 -0.2500 0.22 0.801 -0.2500 1.12 0.895 -0.2500 2.33 0.990 -0.2500 3.28 1.040 -0.2500 4.20 1.013 -0.2500 5.36 0.992 -0.2500 6.27 0.946 -0.2500 7.21 0.970 -0.2500 8.21 1.012 -0.2500 9.24 1.094 -0.2500 10.49 1.631 -0.2500 11.38 1.699 -0.2500 12.55 1.755 -0.2500 13.42 1.774 -0.2500 14.34 1.796 -0.2500 15.33 1.303 -0.2500 16.42 1.234 -0.2500 17.44 1.266 -0.2500 18.44 1.215 -0.2500 19.24 1.281 -0.2500 20.26 1.325 -0.2500 18.91 1.238 -0.2500 18.03 1.257 -0.2500 16.94 1.253 -0.2500 16.05 1.246 -0.2500 15.03 1.344 -0.2500 14.03 1.391 -0.2500 13.27 1.741 -0.2500 12.21 1.705 -0.2500 11.19 1.661 -0.2500 10.24 1.605 -0.2500 9.19 1.530 -0.2500 8.14 1.446 -0.2500 7.18 1.350 -0.2500 6.05 0.905 -0.2500 5.04 0.939 -0.2500 3.91 0.979 -0.2500 2.90 0.977 -0.2500 2.00 0.938 -0.2500 1.00 0.847 -0.2500 -0.03 0.747 -0.2500 -1.02 0.650 -0.2500 -2.11 0.512 -0.2500 -3.15 0.313 -0.2500 -4.16 0.163 -0.2500 -5.35 -0.283 -0.2500 -6.32 -0.313 -0.2500 Tabulated from data in file JG00484.DAT & reduced using program Q01.00L Average Reynolds #: 91300 Number of angles of attack: 53 alpha / Cl / Cm -6.12 -0.281 -0.2500 -5.16 -0.210 -0.2500 -3.99 0.231 -0.2500 -2.99 0.431 -0.2500 -1.91 0.601 -0.2500 -0.89 0.724 -0.2500 0.08 0.814 -0.2500 1.36 0.934 -0.2500 2.13 1.006 -0.2500 3.34 1.115 -0.2500 4.31 1.189 -0.2500 5.27 1.272 -0.2500 6.27 1.351 -0.2500 7.30 1.440 -0.2500 8.50 1.536 -0.2500 9.43 1.598 -0.2500 10.33 1.662 -0.2500 11.49 1.736 -0.2500 12.32 1.755 -0.2500 13.48 1.772 -0.2500 14.31 1.780 -0.2500 15.46 1.768 -0.2500 16.18 1.173 -0.2500 17.49 1.203 -0.2500 18.23 1.220 -0.2500 19.37 1.274 -0.2500 20.48 1.316 -0.2500 18.91 1.261 -0.2500 17.88 1.231 -0.2500 16.95 1.177 -0.2500 16.05 1.188 -0.2500 14.95 1.214 -0.2500 14.09 1.218 -0.2500 13.07 1.268 -0.2500 12.08 1.729 -0.2500 11.22 1.693 -0.2500 10.21 1.637 -0.2500 9.15 1.562 -0.2500 8.08 1.481 -0.2500 7.19 1.411 -0.2500 6.06 1.314 -0.2500 5.00 1.225 -0.2500 3.90 1.136 -0.2500 2.98 1.066 -0.2500 2.04 0.983 -0.2500 0.90 0.871 -0.2500 -0.08 0.772 -0.2500 -1.20 0.670 -0.2500 -2.19 0.541 -0.2500 -3.16 0.367 -0.2500 -4.30 0.156 -0.2500 -5.33 -0.235 -0.2500 -6.35 -0.289 -0.2500 Tabulated from data in file JG00485.DAT & reduced using program Q01.00L Average Reynolds #: 101500 Number of angles of attack: 53 alpha / Cl / Cm -6.23 -0.257 -0.2500 -5.18 -0.122 -0.2500 -3.98 0.339 -0.2500 -3.08 0.501 -0.2500 -2.03 0.664 -0.2500 -1.00 0.764 -0.2500 -0.04 0.850 -0.2500 1.05 0.955 -0.2500 2.09 1.057 -0.2500 3.14 1.159 -0.2500 4.22 1.244 -0.2500 5.23 1.332 -0.2500 6.32 1.428 -0.2500 7.17 1.500 -0.2500 8.28 1.585 -0.2500 9.39 1.663 -0.2500 10.21 1.721 -0.2500 11.19 1.772 -0.2500 12.35 1.786 -0.2500 13.34 1.812 -0.2500 14.27 1.809 -0.2500 15.17 1.797 -0.2500 16.15 1.193 -0.2500 17.38 1.237 -0.2500 18.33 1.225 -0.2500 19.32 1.323 -0.2500 20.40 1.335 -0.2500 19.21 1.268 -0.2500 18.03 1.274 -0.2500 16.99 1.228 -0.2500 15.98 1.207 -0.2500 15.09 1.196 -0.2500 14.15 1.272 -0.2500 13.11 1.260 -0.2500 12.15 1.794 -0.2500 11.21 1.758 -0.2500 10.28 1.716 -0.2500 9.27 1.647 -0.2500 8.23 1.570 -0.2500 7.19 1.486 -0.2500 6.13 1.396 -0.2500 5.10 1.306 -0.2500 4.20 1.228 -0.2500 3.17 1.149 -0.2500 2.11 1.046 -0.2500 1.01 0.936 -0.2500 -0.06 0.832 -0.2500 -1.16 0.733 -0.2500 -2.01 0.651 -0.2500 -3.18 0.461 -0.2500 -4.09 0.292 -0.2500 -5.18 -0.147 -0.2500 -6.15 -0.254 -0.2500 Tabulated from data in file JG00128.DAT & reduced using program Q01.00L Average Reynolds #: 151900 Number of angles of attack: 65 alpha / Cl / Cm -8.09 -0.241 -0.2500 -7.02 -0.248 -0.2500 -6.14 -0.187 -0.2500 -4.87 0.199 -0.2500 -3.84 0.407 -0.2500 -2.61 0.607 -0.2500 -1.69 0.701 -0.2500 -0.52 0.808 -0.2500 0.23 0.879 -0.2500 1.37 0.993 -0.2500 2.48 1.099 -0.2500 3.54 1.193 -0.2500 4.25 1.253 -0.2500 5.38 1.348 -0.2500 6.46 1.445 -0.2500 7.52 1.533 -0.2500 8.50 1.605 -0.2500 9.51 1.679 -0.2500 10.48 1.730 -0.2500 11.42 1.757 -0.2500 12.37 1.780 -0.2500 13.57 1.798 -0.2500 14.49 1.804 -0.2500 15.61 1.809 -0.2500 16.62 1.798 -0.2500 17.40 1.792 -0.2500 18.34 1.762 -0.2500 19.52 1.275 -0.2500 20.47 1.296 -0.2500 21.43 1.343 -0.2500 22.50 1.351 -0.2500 23.21 1.398 -0.2500 24.36 1.483 -0.2500 22.89 1.352 -0.2500 21.93 1.338 -0.2500 21.02 1.309 -0.2500 19.98 1.291 -0.2500 18.95 1.226 -0.2500 17.95 1.233 -0.2500 16.85 1.230 -0.2500 15.77 1.223 -0.2500 14.78 1.253 -0.2500 14.12 1.811 -0.2500 13.06 1.787 -0.2500 12.06 1.762 -0.2500 11.11 1.747 -0.2500 10.02 1.714 -0.2500 9.05 1.646 -0.2500 7.88 1.557 -0.2500 6.87 1.473 -0.2500 5.89 1.390 -0.2500 4.95 1.304 -0.2500 3.97 1.224 -0.2500 2.80 1.117 -0.2500 1.82 1.029 -0.2500 0.85 0.936 -0.2500 -0.16 0.838 -0.2500 -1.20 0.743 -0.2500 -2.26 0.645 -0.2500 -3.39 0.486 -0.2500 -4.50 0.280 -0.2500 -5.50 -0.109 -0.2500 -6.32 -0.215 -0.2500 -7.25 -0.244 -0.2500 -8.20 -0.240 -0.2500 Tabulated from data in file JG00545.DAT & reduced using program Q01.00L Average Reynolds #: 201800 Number of angles of attack: 65 alpha / Cl / Cm -8.39 -0.252 -0.2500 -6.97 -0.225 -0.2500 -5.87 -0.090 -0.2500 -5.29 0.218 -0.2500 -3.98 0.454 -0.2500 -2.97 0.582 -0.2500 -1.81 0.704 -0.2500 -0.86 0.793 -0.2500 0.18 0.895 -0.2500 1.28 1.003 -0.2500 2.33 1.110 -0.2500 3.20 1.192 -0.2500 4.41 1.302 -0.2500 5.51 1.388 -0.2500 6.33 1.460 -0.2500 7.34 1.544 -0.2500 8.60 1.645 -0.2500 9.55 1.712 -0.2500 10.61 1.770 -0.2500 11.50 1.791 -0.2500 12.61 1.816 -0.2500 13.54 1.826 -0.2500 14.73 1.835 -0.2500 15.67 1.840 -0.2500 16.66 1.829 -0.2500 17.67 1.814 -0.2500 18.51 1.806 -0.2500 19.66 1.794 -0.2500 20.69 1.768 -0.2500 21.79 1.760 -0.2500 22.58 1.748 -0.2500 23.48 1.739 -0.2500 24.33 1.709 -0.2500 22.91 1.772 -0.2500 21.83 1.763 -0.2500 20.92 1.778 -0.2500 19.97 1.778 -0.2500 18.93 1.804 -0.2500 17.94 1.815 -0.2500 17.08 1.821 -0.2500 16.13 1.832 -0.2500 15.09 1.841 -0.2500 14.08 1.834 -0.2500 12.99 1.822 -0.2500 12.08 1.802 -0.2500 10.92 1.776 -0.2500 9.81 1.725 -0.2500 8.95 1.665 -0.2500 7.76 1.564 -0.2500 6.88 1.492 -0.2500 5.79 1.401 -0.2500 4.73 1.308 -0.2500 3.96 1.245 -0.2500 2.72 1.129 -0.2500 1.75 1.036 -0.2500 0.89 0.949 -0.2500 -0.22 0.840 -0.2500 -1.10 0.755 -0.2500 -2.12 0.658 -0.2500 -3.11 0.542 -0.2500 -4.40 0.362 -0.2500 -5.23 0.202 -0.2500 -6.38 -0.177 -0.2500 -7.19 -0.236 -0.2500 -8.25 -0.242 -0.2500 Tabulated from data in file JG00544.DAT & reduced using program Q01.00L Average Reynolds #: 252100 Number of angles of attack: 53 alpha / Cl / Cm -5.98 -0.063 -0.2500 -5.30 0.234 -0.2500 -4.17 0.433 -0.2500 -3.14 0.580 -0.2500 -2.13 0.697 -0.2500 -1.07 0.800 -0.2500 -0.06 0.900 -0.2500 0.98 1.007 -0.2500 2.02 1.108 -0.2500 3.05 1.209 -0.2500 4.05 1.304 -0.2500 5.08 1.390 -0.2500 6.11 1.476 -0.2500 7.14 1.563 -0.2500 8.14 1.643 -0.2500 9.17 1.717 -0.2500 10.19 1.773 -0.2500 11.20 1.806 -0.2500 12.26 1.834 -0.2500 13.33 1.852 -0.2500 14.52 1.862 -0.2500 15.49 1.861 -0.2500 16.44 1.856 -0.2500 17.38 1.855 -0.2500 18.27 1.854 -0.2500 19.23 1.831 -0.2500 20.23 1.826 -0.2500 19.15 1.847 -0.2500 18.03 1.840 -0.2500 17.09 1.850 -0.2500 16.09 1.860 -0.2500 15.19 1.858 -0.2500 14.07 1.854 -0.2500 13.08 1.839 -0.2500 12.03 1.819 -0.2500 11.07 1.796 -0.2500 10.13 1.760 -0.2500 9.13 1.705 -0.2500 8.19 1.634 -0.2500 7.16 1.552 -0.2500 6.17 1.470 -0.2500 5.17 1.384 -0.2500 4.14 1.297 -0.2500 3.12 1.201 -0.2500 2.07 1.098 -0.2500 1.04 0.996 -0.2500 0.04 0.896 -0.2500 -0.97 0.795 -0.2500 -2.01 0.694 -0.2500 -3.03 0.576 -0.2500 -4.10 0.424 -0.2500 -5.13 0.244 -0.2500 -6.16 -0.102 -0.2500 Tabulated from data in file AB00489.DAT & reduced using program Q01.00L Average Reynolds #: 302500 Number of angles of attack: 57 alpha / Cl / Cm -8.09 -0.240 -0.2500 -7.19 -0.193 -0.2500 -6.07 -0.060 -0.2500 -5.14 0.280 -0.2500 -4.15 0.436 -0.2500 -3.08 0.575 -0.2500 -2.05 0.688 -0.2500 -1.04 0.788 -0.2500 -0.00 0.894 -0.2500 1.02 0.998 -0.2500 2.05 1.101 -0.2500 3.09 1.205 -0.2500 4.11 1.301 -0.2500 5.13 1.394 -0.2500 6.15 1.477 -0.2500 7.16 1.561 -0.2500 8.20 1.642 -0.2500 9.17 1.708 -0.2500 10.21 1.765 -0.2500 11.23 1.798 -0.2500 12.23 1.824 -0.2500 13.19 1.842 -0.2500 14.16 1.851 -0.2500 15.17 1.854 -0.2500 16.20 1.841 -0.2500 17.19 1.836 -0.2500 18.20 1.840 -0.2500 19.19 1.836 -0.2500 20.21 1.881 -0.2500 19.27 1.839 -0.2500 18.24 1.843 -0.2500 17.30 1.836 -0.2500 16.19 1.845 -0.2500 15.14 1.845 -0.2500 14.10 1.842 -0.2500 13.18 1.835 -0.2500 12.19 1.817 -0.2500 11.25 1.791 -0.2500 10.19 1.755 -0.2500 9.21 1.704 -0.2500 8.16 1.629 -0.2500 7.17 1.548 -0.2500 6.15 1.462 -0.2500 5.12 1.376 -0.2500 4.08 1.281 -0.2500 3.09 1.184 -0.2500 2.07 1.082 -0.2500 1.02 0.975 -0.2500 0.02 0.873 -0.2500 -0.99 0.771 -0.2500 -2.04 0.670 -0.2500 -3.08 0.552 -0.2500 -4.09 0.419 -0.2500 -5.14 0.249 -0.2500 -6.27 -0.107 -0.2500 -7.15 -0.199 -0.2500 -8.13 -0.256 -0.2500 Tabulated from data in file JG00494.DAT & reduced using program Q01.00L File s1210.lft created on 12-05-1997 at 15:25:51 using program FORMAT :::::::::::::: S1223.LFT :::::::::::::: 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 :::::::::::::: S1223GF1.LFT :::::::::::::: Airfoil: S1223 Builder: Y. Tinel Comment: gurney flap (h/c = 1.04%) Number of Reynolds #'s: 1 Average Reynolds #: 201300 Number of angles of attack: 27 alpha / Cl / Cm -6.61 -0.113 -0.2900 -5.67 0.033 -0.2900 -4.45 0.245 -0.2900 -3.46 0.434 -0.2900 -2.27 1.030 -0.2900 -1.45 1.127 -0.2900 -0.46 1.240 -0.2900 0.52 1.337 -0.2900 1.54 1.434 -0.2900 2.66 1.538 -0.2900 3.76 1.623 -0.2900 4.81 1.665 -0.2900 5.97 1.754 -0.2900 6.93 1.823 -0.2900 7.90 1.888 -0.2900 9.00 1.962 -0.2900 10.12 2.033 -0.2900 11.14 2.090 -0.2900 12.01 2.138 -0.2900 13.09 2.187 -0.2900 14.03 2.232 -0.2900 15.10 2.271 -0.2900 16.02 2.284 -0.2900 17.09 2.251 -0.2900 17.94 2.173 -0.2900 19.05 2.095 -0.2900 19.95 2.063 -0.2900 Tabulated from data in file PG00515.DAT & reduced using program Q01.00L File s1223gf1.lft created on 12-05-1997 at 15:25:51 using program FORMAT :::::::::::::: S1223VG1.LFT :::::::::::::: Airfoil: S1223 Builder: Y. Tinel Comment: upper surface vortex generator type "A" @ x/c = 17% Number of Reynolds #'s: 7 Average Reynolds #: 59800 Number of angles of attack: 65 alpha / Cl / Cm -8.87 -0.151 -0.2900 -7.77 -0.117 -0.2900 -6.84 -0.090 -0.2900 -5.78 -0.032 -0.2900 -4.84 0.033 -0.2900 -3.80 0.172 -0.2900 -2.70 0.398 -0.2900 -1.67 0.712 -0.2900 -0.61 0.844 -0.2900 0.38 0.950 -0.2900 1.48 1.047 -0.2900 2.43 1.086 -0.2900 3.44 1.126 -0.2900 4.50 1.206 -0.2900 5.50 1.270 -0.2900 6.51 1.358 -0.2900 7.57 1.429 -0.2900 8.60 1.495 -0.2900 9.56 1.539 -0.2900 10.61 1.596 -0.2900 11.58 1.639 -0.2900 12.62 1.697 -0.2900 13.68 1.772 -0.2900 14.69 1.807 -0.2900 15.67 1.860 -0.2900 16.56 1.418 -0.2900 17.52 1.370 -0.2900 18.52 1.435 -0.2900 19.54 1.480 -0.2900 20.56 1.489 -0.2900 21.55 1.523 -0.2900 22.60 1.544 -0.2900 23.58 1.567 -0.2900 22.70 1.577 -0.2900 21.68 1.489 -0.2900 20.69 1.469 -0.2900 19.76 1.475 -0.2900 18.75 1.422 -0.2900 17.66 1.361 -0.2900 16.65 1.330 -0.2900 15.65 1.296 -0.2900 14.71 1.204 -0.2900 13.66 1.210 -0.2900 12.73 1.279 -0.2900 11.71 1.293 -0.2900 10.69 1.356 -0.2900 9.82 1.571 -0.2900 8.74 1.513 -0.2900 7.79 1.449 -0.2900 6.76 1.384 -0.2900 5.72 1.310 -0.2900 4.77 1.229 -0.2900 3.71 1.152 -0.2900 2.69 1.112 -0.2900 1.69 1.060 -0.2900 0.63 0.982 -0.2900 -0.37 0.871 -0.2900 -1.41 0.751 -0.2900 -2.49 0.486 -0.2900 -3.60 0.193 -0.2900 -4.59 0.062 -0.2900 -5.61 -0.033 -0.2900 -6.65 -0.084 -0.2900 -7.68 -0.116 -0.2900 -8.69 -0.151 -0.2900 Tabulated from data in file MS00354.DAT & reduced using program Q01.00L Average Reynolds #: 79600 Number of angles of attack: 65 alpha / Cl / Cm -9.19 -0.110 -0.2900 -7.84 -0.065 -0.2900 -6.81 -0.027 -0.2900 -5.86 0.017 -0.2900 -4.76 0.082 -0.2900 -3.72 0.207 -0.2900 -2.65 0.487 -0.2900 -1.57 0.774 -0.2900 -0.58 0.893 -0.2900 0.47 0.990 -0.2900 1.44 1.066 -0.2900 2.53 1.161 -0.2900 3.55 1.230 -0.2900 4.56 1.265 -0.2900 5.56 1.345 -0.2900 6.54 1.402 -0.2900 7.63 1.516 -0.2900 8.60 1.575 -0.2900 9.62 1.637 -0.2900 10.62 1.697 -0.2900 11.69 1.748 -0.2900 12.64 1.780 -0.2900 13.68 1.864 -0.2900 14.76 1.923 -0.2900 15.70 1.957 -0.2900 16.72 1.999 -0.2900 17.52 1.314 -0.2900 18.54 1.326 -0.2900 19.58 1.373 -0.2900 20.57 1.429 -0.2900 21.58 1.406 -0.2900 22.57 1.481 -0.2900 23.59 1.527 -0.2900 22.79 1.543 -0.2900 21.72 1.444 -0.2900 20.73 1.414 -0.2900 19.70 1.373 -0.2900 18.72 1.328 -0.2900 17.65 1.316 -0.2900 16.76 1.292 -0.2900 15.71 1.393 -0.2900 14.74 1.512 -0.2900 13.77 1.499 -0.2900 12.74 1.452 -0.2900 11.80 1.727 -0.2900 10.79 1.681 -0.2900 9.75 1.612 -0.2900 8.80 1.565 -0.2900 7.71 1.478 -0.2900 6.77 1.400 -0.2900 5.74 1.313 -0.2900 4.69 1.259 -0.2900 3.74 1.233 -0.2900 2.70 1.159 -0.2900 1.65 1.068 -0.2900 0.64 0.990 -0.2900 -0.37 0.899 -0.2900 -1.45 0.770 -0.2900 -2.46 0.584 -0.2900 -3.59 0.193 -0.2900 -4.64 0.071 -0.2900 -5.65 0.010 -0.2900 -6.64 -0.033 -0.2900 -7.69 -0.072 -0.2900 -8.73 -0.107 -0.2900 Tabulated from data in file MS00353.DAT & reduced using program Q01.00L Average Reynolds #: 98400 Number of angles of attack: 65 alpha / Cl / Cm -8.89 -0.074 -0.2900 -7.76 -0.030 -0.2900 -6.84 0.009 -0.2900 -5.80 0.043 -0.2900 -4.83 0.100 -0.2900 -3.78 0.211 -0.2900 -2.76 0.431 -0.2900 -1.66 0.794 -0.2900 -0.64 0.917 -0.2900 0.40 1.021 -0.2900 1.54 1.114 -0.2900 2.50 1.200 -0.2900 3.50 1.271 -0.2900 4.49 1.327 -0.2900 5.52 1.392 -0.2900 6.54 1.490 -0.2900 7.59 1.560 -0.2900 8.61 1.633 -0.2900 9.61 1.691 -0.2900 10.64 1.759 -0.2900 11.67 1.806 -0.2900 12.70 1.873 -0.2900 13.69 1.926 -0.2900 14.67 1.970 -0.2900 15.72 2.016 -0.2900 16.72 2.041 -0.2900 17.50 1.279 -0.2900 18.55 1.322 -0.2900 19.56 1.374 -0.2900 20.55 1.404 -0.2900 21.55 1.476 -0.2900 22.57 1.546 -0.2900 23.58 1.526 -0.2900 22.73 1.524 -0.2900 21.78 1.469 -0.2900 20.64 1.409 -0.2900 19.65 1.372 -0.2900 18.62 1.316 -0.2900 17.63 1.310 -0.2900 16.69 1.325 -0.2900 15.65 1.224 -0.2900 14.67 1.409 -0.2900 13.67 1.412 -0.2900 12.78 1.868 -0.2900 11.75 1.814 -0.2900 10.87 1.760 -0.2900 9.82 1.694 -0.2900 8.80 1.633 -0.2900 7.79 1.562 -0.2900 6.78 1.498 -0.2900 5.82 1.421 -0.2900 4.75 1.333 -0.2900 3.72 1.278 -0.2900 2.64 1.194 -0.2900 1.57 1.103 -0.2900 0.57 1.025 -0.2900 -0.35 0.943 -0.2900 -1.36 0.821 -0.2900 -2.53 0.586 -0.2900 -3.57 0.226 -0.2900 -4.59 0.109 -0.2900 -5.59 0.037 -0.2900 -6.63 0.009 -0.2900 -7.65 -0.021 -0.2900 -8.68 -0.059 -0.2900 Tabulated from data in file MS00352.DAT & reduced using program Q01.00L Average Reynolds #: 123900 Number of angles of attack: 65 alpha / Cl / Cm -8.64 -0.035 -0.2900 -7.79 -0.008 -0.2900 -6.75 0.024 -0.2900 -5.82 0.057 -0.2900 -4.77 0.117 -0.2900 -3.77 0.230 -0.2900 -2.70 0.452 -0.2900 -1.53 0.825 -0.2900 -0.54 0.940 -0.2900 0.57 1.054 -0.2900 1.46 1.127 -0.2900 2.54 1.221 -0.2900 3.50 1.293 -0.2900 4.50 1.356 -0.2900 5.52 1.442 -0.2900 6.54 1.518 -0.2900 7.61 1.585 -0.2900 8.52 1.647 -0.2900 9.62 1.714 -0.2900 10.63 1.760 -0.2900 11.67 1.809 -0.2900 12.72 1.872 -0.2900 13.69 1.927 -0.2900 14.71 1.980 -0.2900 15.72 2.031 -0.2900 16.75 2.078 -0.2900 17.70 2.102 -0.2900 18.46 1.338 -0.2900 19.55 1.364 -0.2900 20.46 1.379 -0.2900 21.60 1.449 -0.2900 22.52 1.472 -0.2900 23.55 1.538 -0.2900 22.74 1.491 -0.2900 21.81 1.454 -0.2900 20.67 1.388 -0.2900 19.69 1.336 -0.2900 18.68 1.331 -0.2900 17.67 1.291 -0.2900 16.63 1.279 -0.2900 15.73 1.406 -0.2900 14.72 1.412 -0.2900 13.81 1.546 -0.2900 12.88 1.896 -0.2900 11.86 1.837 -0.2900 10.86 1.786 -0.2900 9.84 1.719 -0.2900 8.85 1.652 -0.2900 7.83 1.593 -0.2900 6.88 1.521 -0.2900 5.85 1.455 -0.2900 4.76 1.365 -0.2900 3.77 1.304 -0.2900 2.77 1.231 -0.2900 1.75 1.138 -0.2900 0.74 1.050 -0.2900 -0.29 0.957 -0.2900 -1.32 0.835 -0.2900 -2.38 0.683 -0.2900 -3.49 0.263 -0.2900 -4.56 0.125 -0.2900 -5.59 0.058 -0.2900 -6.61 0.033 -0.2900 -7.61 -0.009 -0.2900 -8.68 -0.031 -0.2900 Tabulated from data in file MS00346.DAT & reduced using program Q01.00L Average Reynolds #: 147900 Number of angles of attack: 65 alpha / Cl / Cm -8.88 -0.005 -0.2900 -7.75 0.017 -0.2900 -6.73 0.041 -0.2900 -5.75 0.075 -0.2900 -4.79 0.128 -0.2900 -3.76 0.242 -0.2900 -2.71 0.543 -0.2900 -1.57 0.839 -0.2900 -0.49 0.968 -0.2900 0.53 1.071 -0.2900 1.53 1.158 -0.2900 2.55 1.244 -0.2900 3.56 1.324 -0.2900 4.60 1.404 -0.2900 5.60 1.486 -0.2900 6.60 1.560 -0.2900 7.61 1.630 -0.2900 8.67 1.705 -0.2900 9.70 1.774 -0.2900 10.71 1.830 -0.2900 11.73 1.892 -0.2900 12.66 1.933 -0.2900 13.73 1.977 -0.2900 14.75 2.036 -0.2900 15.80 2.092 -0.2900 16.71 2.136 -0.2900 17.71 2.155 -0.2900 18.72 2.182 -0.2900 19.74 2.191 -0.2900 20.59 1.398 -0.2900 21.54 1.465 -0.2900 22.57 1.487 -0.2900 23.54 1.512 -0.2900 22.79 1.479 -0.2900 21.68 1.410 -0.2900 20.77 1.414 -0.2900 19.77 1.371 -0.2900 18.76 1.344 -0.2900 17.75 1.350 -0.2900 16.81 1.443 -0.2900 15.81 1.539 -0.2900 14.92 2.071 -0.2900 13.80 2.004 -0.2900 12.81 1.945 -0.2900 11.79 1.886 -0.2900 10.85 1.838 -0.2900 9.73 1.759 -0.2900 8.78 1.695 -0.2900 7.72 1.618 -0.2900 6.83 1.561 -0.2900 5.78 1.482 -0.2900 4.80 1.405 -0.2900 3.64 1.314 -0.2900 2.66 1.241 -0.2900 1.70 1.155 -0.2900 0.66 1.064 -0.2900 -0.36 0.959 -0.2900 -1.43 0.832 -0.2900 -2.42 0.694 -0.2900 -3.55 0.251 -0.2900 -4.65 0.116 -0.2900 -5.71 0.067 -0.2900 -6.71 0.036 -0.2900 -7.73 0.010 -0.2900 -8.74 -0.012 -0.2900 Tabulated from data in file MS00350.DAT & reduced using program Q01.00L Average Reynolds #: 173200 Number of angles of attack: 65 alpha / Cl / Cm -8.86 0.000 -0.2900 -7.79 0.029 -0.2900 -6.81 0.047 -0.2900 -5.77 0.079 -0.2900 -4.84 0.127 -0.2900 -3.79 0.216 -0.2900 -2.72 0.496 -0.2900 -1.41 0.864 -0.2900 -0.42 0.980 -0.2900 0.61 1.088 -0.2900 1.64 1.180 -0.2900 2.54 1.257 -0.2900 3.58 1.344 -0.2900 4.55 1.415 -0.2900 5.56 1.494 -0.2900 6.60 1.578 -0.2900 7.60 1.652 -0.2900 8.70 1.727 -0.2900 9.60 1.792 -0.2900 10.73 1.863 -0.2900 11.62 1.917 -0.2900 12.62 1.961 -0.2900 13.69 2.023 -0.2900 14.68 2.070 -0.2900 15.66 2.127 -0.2900 16.72 2.174 -0.2900 17.65 2.200 -0.2900 18.75 2.224 -0.2900 19.31 1.745 -0.2900 20.47 1.387 -0.2900 21.64 1.440 -0.2900 22.48 1.483 -0.2900 23.46 1.528 -0.2900 22.57 1.482 -0.2900 21.58 1.444 -0.2900 20.40 1.393 -0.2900 19.43 1.379 -0.2900 18.42 1.430 -0.2900 17.56 1.418 -0.2900 16.62 1.499 -0.2900 15.65 1.635 -0.2900 14.85 2.099 -0.2900 13.85 2.037 -0.2900 12.89 1.989 -0.2900 11.79 1.925 -0.2900 10.81 1.861 -0.2900 9.78 1.793 -0.2900 8.83 1.724 -0.2900 7.81 1.658 -0.2900 6.68 1.576 -0.2900 5.65 1.500 -0.2900 4.71 1.424 -0.2900 3.58 1.338 -0.2900 2.62 1.260 -0.2900 1.65 1.172 -0.2900 0.64 1.080 -0.2900 -0.39 0.972 -0.2900 -1.45 0.846 -0.2900 -2.41 0.715 -0.2900 -3.58 0.245 -0.2900 -4.65 0.128 -0.2900 -5.55 0.088 -0.2900 -6.59 0.060 -0.2900 -7.59 0.022 -0.2900 -8.64 0.003 -0.2900 Tabulated from data in file MS00351.DAT & reduced using program Q01.00L Average Reynolds #: 197200 Number of angles of attack: 65 alpha / Cl / Cm -9.24 -0.004 -0.2900 -7.85 0.032 -0.2900 -6.82 0.049 -0.2900 -5.81 0.076 -0.2900 -4.76 0.113 -0.2900 -3.85 0.208 -0.2900 -2.68 0.480 -0.2900 -1.54 0.828 -0.2900 -0.49 0.953 -0.2900 0.64 1.071 -0.2900 1.67 1.165 -0.2900 2.56 1.243 -0.2900 3.64 1.337 -0.2900 4.76 1.422 -0.2900 5.71 1.500 -0.2900 6.73 1.576 -0.2900 7.74 1.651 -0.2900 8.70 1.718 -0.2900 9.76 1.788 -0.2900 10.78 1.851 -0.2900 11.74 1.907 -0.2900 12.75 1.958 -0.2900 13.75 2.016 -0.2900 14.72 2.080 -0.2900 15.78 2.140 -0.2900 16.73 2.173 -0.2900 17.77 2.216 -0.2900 18.82 2.249 -0.2900 19.76 2.271 -0.2900 20.49 1.384 -0.2900 21.42 1.408 -0.2900 22.52 1.468 -0.2900 23.56 1.477 -0.2900 22.69 1.472 -0.2900 21.65 1.414 -0.2900 20.71 1.369 -0.2900 19.68 1.345 -0.2900 18.75 1.377 -0.2900 17.68 1.467 -0.2900 16.79 1.554 -0.2900 16.08 2.165 -0.2900 14.89 2.102 -0.2900 13.91 2.041 -0.2900 12.78 1.987 -0.2900 11.89 1.931 -0.2900 10.83 1.868 -0.2900 9.72 1.786 -0.2900 8.71 1.712 -0.2900 7.57 1.636 -0.2900 6.67 1.562 -0.2900 5.42 1.469 -0.2900 4.59 1.401 -0.2900 3.69 1.334 -0.2900 2.62 1.244 -0.2900 1.63 1.151 -0.2900 0.58 1.054 -0.2900 -0.51 0.936 -0.2900 -1.52 0.816 -0.2900 -2.51 0.677 -0.2900 -3.52 0.233 -0.2900 -4.59 0.122 -0.2900 -5.59 0.075 -0.2900 -6.59 0.042 -0.2900 -7.64 0.017 -0.2900 -8.64 0.004 -0.2900 Tabulated from data in file MS00344.DAT & reduced using program Q01.00L File s1223vg1.lft created on 12-05-1997 at 15:25:51 using program FORMAT :::::::::::::: S6062.LFT :::::::::::::: Airfoil: S6062 Builder: B. Matheson Comment: clean Number of Reynolds #'s: 3 Average Reynolds #: 101900 Number of angles of attack: 33 alpha / Cl / Cm -5.76 -0.348 -0.0400 -3.98 -0.199 -0.0400 -2.27 -0.055 -0.0400 -0.60 0.091 -0.0400 0.68 0.232 -0.0400 2.40 0.509 -0.0400 3.55 0.620 -0.0400 5.33 0.769 -0.0400 7.05 0.877 -0.0400 8.25 0.950 -0.0400 9.82 1.024 -0.0400 11.54 1.038 -0.0400 12.67 1.000 -0.0400 14.37 0.952 -0.0400 16.08 0.946 -0.0400 17.32 0.943 -0.0400 19.04 0.956 -0.0400 16.86 0.939 -0.0400 15.27 0.943 -0.0400 13.65 0.966 -0.0400 12.21 1.023 -0.0400 10.78 1.028 -0.0400 9.40 1.007 -0.0400 7.80 0.909 -0.0400 6.40 0.813 -0.0400 4.79 0.710 -0.0400 3.26 0.575 -0.0400 1.62 0.378 -0.0400 0.12 0.152 -0.0400 -1.39 -0.014 -0.0400 -2.88 -0.113 -0.0400 -4.34 -0.237 -0.0400 -5.91 -0.366 -0.0400 Tabulated from data in file AB00141.DAT & reduced using program Q01.00L Average Reynolds #: 203100 Number of angles of attack: 33 alpha / Cl / Cm -6.86 -0.454 -0.0400 -2.80 -0.079 -0.0400 -2.64 -0.067 -0.0400 -0.74 0.149 -0.0400 0.50 0.300 -0.0400 2.41 0.506 -0.0400 3.65 0.633 -0.0400 5.50 0.776 -0.0400 6.75 0.868 -0.0400 8.59 0.988 -0.0400 9.69 1.058 -0.0400 11.33 1.105 -0.0400 12.85 1.093 -0.0400 14.52 1.076 -0.0400 16.03 1.049 -0.0400 17.49 1.044 -0.0400 18.60 0.939 -0.0400 16.85 1.004 -0.0400 14.90 1.047 -0.0400 13.75 1.094 -0.0400 11.98 1.097 -0.0400 10.97 1.090 -0.0400 9.46 1.041 -0.0400 7.98 0.941 -0.0400 6.43 0.835 -0.0400 4.73 0.718 -0.0400 3.07 0.569 -0.0400 1.90 0.445 -0.0400 0.08 0.243 -0.0400 -1.13 0.093 -0.0400 -3.00 -0.110 -0.0400 -4.21 -0.219 -0.0400 -6.18 -0.388 -0.0400 Tabulated from data in file AB00139.DAT & reduced using program Q01.00L Average Reynolds #: 304000 Number of angles of attack: 33 alpha / Cl / Cm -5.67 -0.336 -0.0400 -4.01 -0.189 -0.0400 -2.62 -0.037 -0.0400 -0.86 0.171 -0.0400 0.64 0.322 -0.0400 2.48 0.511 -0.0400 3.78 0.638 -0.0400 5.76 0.792 -0.0400 7.12 0.896 -0.0400 8.55 0.998 -0.0400 9.99 1.081 -0.0400 11.28 1.105 -0.0400 12.70 1.126 -0.0400 13.85 1.097 -0.0400 15.48 1.053 -0.0400 17.07 1.066 -0.0400 18.46 1.074 -0.0400 16.91 1.068 -0.0400 15.58 1.058 -0.0400 13.76 1.112 -0.0400 12.67 1.109 -0.0400 10.84 1.096 -0.0400 9.50 1.056 -0.0400 8.04 0.958 -0.0400 6.48 0.848 -0.0400 4.70 0.703 -0.0400 3.19 0.575 -0.0400 1.26 0.378 -0.0400 0.03 0.253 -0.0400 -1.57 0.083 -0.0400 -2.71 -0.056 -0.0400 -4.51 -0.245 -0.0400 -5.81 -0.357 -0.0400 Tabulated from data in file AB00137.DAT & reduced using program Q01.00L File s6062.lft created on 12-05-1997 at 15:25:51 using program FORMAT :::::::::::::: S7012B.LFT :::::::::::::: Airfoil: S7012 (B) Builder: M. Lachowski Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 61100 Number of angles of attack: 33 alpha / Cl / Cm -5.84 -0.411 -0.0400 -4.31 -0.292 -0.0400 -2.74 -0.151 -0.0400 -1.25 -0.043 -0.0400 0.14 0.114 -0.0400 1.74 0.376 -0.0400 3.49 0.561 -0.0400 4.86 0.684 -0.0400 6.37 0.813 -0.0400 7.89 0.942 -0.0400 9.55 1.034 -0.0400 10.98 1.084 -0.0400 12.60 1.097 -0.0400 13.84 1.036 -0.0400 15.53 0.990 -0.0400 16.91 0.953 -0.0400 18.44 0.997 -0.0400 17.05 0.994 -0.0400 15.60 0.997 -0.0400 14.10 1.032 -0.0400 12.66 1.096 -0.0400 11.06 1.089 -0.0400 9.64 1.047 -0.0400 8.01 0.953 -0.0400 6.60 0.841 -0.0400 4.99 0.698 -0.0400 3.54 0.570 -0.0400 1.88 0.404 -0.0400 0.35 0.142 -0.0400 -1.25 -0.043 -0.0400 -2.61 -0.132 -0.0400 -4.20 -0.276 -0.0400 -5.84 -0.410 -0.0400 Tabulated from data in file AB00093.DAT & reduced using program Q01.00L Average Reynolds #: 102000 Number of angles of attack: 33 alpha / Cl / Cm -5.88 -0.459 -0.0400 -4.40 -0.329 -0.0400 -2.88 -0.192 -0.0400 -1.30 -0.057 -0.0400 0.27 0.177 -0.0400 1.79 0.355 -0.0400 3.32 0.504 -0.0400 4.80 0.651 -0.0400 6.42 0.813 -0.0400 7.97 0.939 -0.0400 9.54 1.030 -0.0400 10.99 1.078 -0.0400 12.54 1.051 -0.0400 13.86 0.973 -0.0400 15.46 0.948 -0.0400 16.92 0.929 -0.0400 18.47 0.929 -0.0400 17.15 0.927 -0.0400 15.57 0.928 -0.0400 14.18 0.968 -0.0400 12.53 1.017 -0.0400 11.09 1.083 -0.0400 9.66 1.031 -0.0400 8.02 0.933 -0.0400 6.55 0.820 -0.0400 5.03 0.664 -0.0400 3.53 0.517 -0.0400 1.92 0.361 -0.0400 0.44 0.198 -0.0400 -1.13 -0.060 -0.0400 -2.68 -0.174 -0.0400 -4.31 -0.320 -0.0400 -5.83 -0.456 -0.0400 Tabulated from data in file AB00091.DAT & reduced using program Q01.00L Average Reynolds #: 152600 Number of angles of attack: 33 alpha / Cl / Cm -5.94 -0.423 -0.0400 -4.16 -0.258 -0.0400 -2.60 -0.117 -0.0400 -1.10 0.040 -0.0400 0.51 0.233 -0.0400 1.96 0.380 -0.0400 3.43 0.537 -0.0400 5.12 0.713 -0.0400 6.67 0.862 -0.0400 8.10 0.969 -0.0400 9.67 1.060 -0.0400 11.18 1.107 -0.0400 12.68 1.062 -0.0400 14.31 0.996 -0.0400 15.61 0.991 -0.0400 17.11 0.990 -0.0400 18.83 0.990 -0.0400 16.73 0.981 -0.0400 15.28 1.006 -0.0400 13.89 0.997 -0.0400 12.35 1.081 -0.0400 10.98 1.099 -0.0400 9.49 1.045 -0.0400 7.92 0.950 -0.0400 6.29 0.820 -0.0400 4.91 0.681 -0.0400 3.34 0.515 -0.0400 1.83 0.357 -0.0400 0.12 0.183 -0.0400 -1.26 0.004 -0.0400 -2.90 -0.152 -0.0400 -4.30 -0.278 -0.0400 -6.09 -0.436 -0.0400 Tabulated from data in file PG00564.DAT & reduced using program Q01.00L Average Reynolds #: 203200 Number of angles of attack: 33 alpha / Cl / Cm -5.90 -0.430 -0.0400 -4.40 -0.292 -0.0400 -2.83 -0.146 -0.0400 -1.35 0.015 -0.0400 0.16 0.169 -0.0400 1.76 0.341 -0.0400 3.34 0.510 -0.0400 4.80 0.663 -0.0400 6.45 0.826 -0.0400 7.98 0.943 -0.0400 9.51 1.038 -0.0400 11.00 1.085 -0.0400 12.51 1.074 -0.0400 14.00 1.003 -0.0400 15.34 0.991 -0.0400 16.89 0.929 -0.0400 18.27 0.917 -0.0400 16.75 0.932 -0.0400 15.50 0.955 -0.0400 13.93 1.001 -0.0400 12.51 1.090 -0.0400 11.14 1.089 -0.0400 9.52 1.036 -0.0400 8.02 0.944 -0.0400 6.45 0.824 -0.0400 4.98 0.680 -0.0400 3.50 0.524 -0.0400 1.96 0.357 -0.0400 0.42 0.196 -0.0400 -1.25 0.024 -0.0400 -2.79 -0.149 -0.0400 -4.21 -0.282 -0.0400 -5.90 -0.434 -0.0400 Tabulated from data in file AB00089.DAT & reduced using program Q01.00L Average Reynolds #: 304700 Number of angles of attack: 33 alpha / Cl / Cm -5.89 -0.440 -0.0400 -4.27 -0.286 -0.0400 -2.70 -0.123 -0.0400 -1.18 0.045 -0.0400 0.24 0.179 -0.0400 1.74 0.347 -0.0400 3.35 0.524 -0.0400 4.89 0.692 -0.0400 6.55 0.856 -0.0400 7.86 0.966 -0.0400 9.61 1.081 -0.0400 11.04 1.137 -0.0400 12.43 1.143 -0.0400 13.80 1.111 -0.0400 15.42 1.003 -0.0400 16.80 0.960 -0.0400 18.36 0.962 -0.0400 16.94 0.953 -0.0400 15.42 0.998 -0.0400 14.04 1.079 -0.0400 12.66 1.135 -0.0400 11.11 1.138 -0.0400 9.53 1.074 -0.0400 8.04 0.976 -0.0400 6.55 0.852 -0.0400 4.85 0.683 -0.0400 3.31 0.516 -0.0400 1.80 0.349 -0.0400 0.32 0.180 -0.0400 -1.33 0.025 -0.0400 -2.95 -0.162 -0.0400 -4.49 -0.314 -0.0400 -6.21 -0.476 -0.0400 Tabulated from data in file AB00087.DAT & reduced using program Q01.00L File s7012b.lft created on 12-05-1997 at 15:25:51 using program FORMAT :::::::::::::: S7055.LFT :::::::::::::: Airfoil: S7055 Builder: G. Jones Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 61100 Number of angles of attack: 33 alpha / Cl / Cm -4.54 -0.203 -0.0680 -2.71 0.001 -0.0680 -0.81 0.188 -0.0680 0.42 0.337 -0.0680 2.28 0.525 -0.0680 3.50 0.668 -0.0680 5.23 0.840 -0.0680 6.50 0.959 -0.0680 8.34 1.114 -0.0680 9.62 1.195 -0.0680 11.37 1.237 -0.0680 12.61 1.230 -0.0680 14.20 1.206 -0.0680 15.90 1.175 -0.0680 17.15 1.127 -0.0680 18.88 1.052 -0.0680 20.22 1.020 -0.0680 18.22 1.101 -0.0680 16.63 1.181 -0.0680 15.16 1.178 -0.0680 13.76 1.179 -0.0680 12.35 1.207 -0.0680 10.53 1.207 -0.0680 8.88 1.120 -0.0680 7.73 1.028 -0.0680 6.16 0.902 -0.0680 4.50 0.743 -0.0680 2.94 0.582 -0.0680 1.35 0.402 -0.0680 -0.27 0.230 -0.0680 -1.74 0.065 -0.0680 -3.30 -0.094 -0.0680 -4.79 -0.261 -0.0680 Tabulated from data in file JG00151.DAT & reduced using program Q01.00L Average Reynolds #: 101600 Number of angles of attack: 33 alpha / Cl / Cm -4.39 -0.089 -0.0680 -2.37 0.139 -0.0680 -0.90 0.290 -0.0680 0.42 0.421 -0.0680 2.29 0.598 -0.0680 3.54 0.719 -0.0680 5.38 0.901 -0.0680 6.63 1.017 -0.0680 7.94 1.126 -0.0680 9.89 1.232 -0.0680 11.14 1.225 -0.0680 12.96 1.200 -0.0680 14.09 1.194 -0.0680 15.83 1.163 -0.0680 16.99 1.089 -0.0680 18.90 1.004 -0.0680 20.30 1.033 -0.0680 18.10 1.014 -0.0680 16.50 1.166 -0.0680 15.03 1.170 -0.0680 13.68 1.186 -0.0680 12.37 1.196 -0.0680 10.85 1.214 -0.0680 9.37 1.206 -0.0680 7.84 1.108 -0.0680 6.32 0.975 -0.0680 4.62 0.810 -0.0680 3.09 0.657 -0.0680 1.42 0.496 -0.0680 -0.25 0.335 -0.0680 -1.79 0.173 -0.0680 -3.49 0.007 -0.0680 -4.58 -0.123 -0.0680 Tabulated from data in file AB00149.DAT & reduced using program Q01.00L Average Reynolds #: 152200 Number of angles of attack: 33 alpha / Cl / Cm -4.65 -0.072 -0.0680 -2.73 0.099 -0.0680 -1.14 0.240 -0.0680 0.36 0.389 -0.0680 1.87 0.542 -0.0680 3.53 0.713 -0.0680 4.96 0.861 -0.0680 6.59 1.019 -0.0680 8.13 1.142 -0.0680 9.79 1.219 -0.0680 11.01 1.223 -0.0680 12.50 1.213 -0.0680 13.97 1.204 -0.0680 15.65 1.173 -0.0680 17.16 1.069 -0.0680 18.50 1.041 -0.0680 20.35 1.027 -0.0680 17.37 1.049 -0.0680 16.51 1.101 -0.0680 15.14 1.186 -0.0680 13.79 1.206 -0.0680 12.17 1.214 -0.0680 10.79 1.216 -0.0680 9.30 1.204 -0.0680 7.82 1.113 -0.0680 6.22 0.978 -0.0680 4.72 0.826 -0.0680 3.14 0.663 -0.0680 1.49 0.493 -0.0680 -0.03 0.342 -0.0680 -1.53 0.197 -0.0680 -3.02 0.067 -0.0680 -4.66 -0.076 -0.0680 Tabulated from data in file AB00536.DAT & reduced using program Q01.00L Average Reynolds #: 202800 Number of angles of attack: 33 alpha / Cl / Cm -4.57 -0.059 -0.0680 -2.43 0.128 -0.0680 -0.93 0.261 -0.0680 0.45 0.404 -0.0680 2.38 0.607 -0.0680 3.69 0.747 -0.0680 5.09 0.890 -0.0680 6.99 1.063 -0.0680 8.36 1.166 -0.0680 9.68 1.204 -0.0680 11.54 1.207 -0.0680 12.69 1.205 -0.0680 14.45 1.183 -0.0680 15.50 1.163 -0.0680 17.00 1.080 -0.0680 18.63 1.037 -0.0680 20.30 1.015 -0.0680 17.73 1.042 -0.0680 16.51 1.140 -0.0680 14.95 1.176 -0.0680 13.64 1.197 -0.0680 12.24 1.205 -0.0680 10.82 1.204 -0.0680 9.31 1.199 -0.0680 7.58 1.104 -0.0680 6.03 0.970 -0.0680 4.30 0.798 -0.0680 3.12 0.674 -0.0680 1.34 0.487 -0.0680 0.05 0.354 -0.0680 -1.85 0.169 -0.0680 -3.25 0.046 -0.0680 -4.68 -0.081 -0.0680 Tabulated from data in file AB00147.DAT & reduced using program Q01.00L Average Reynolds #: 303800 Number of angles of attack: 33 alpha / Cl / Cm -4.41 -0.067 -0.0680 -2.82 0.079 -0.0680 -1.23 0.226 -0.0680 0.29 0.385 -0.0680 2.05 0.570 -0.0680 3.87 0.763 -0.0680 5.23 0.901 -0.0680 6.47 1.015 -0.0680 8.03 1.133 -0.0680 10.06 1.196 -0.0680 11.37 1.203 -0.0680 12.54 1.201 -0.0680 14.14 1.188 -0.0680 15.87 1.146 -0.0680 16.82 1.155 -0.0680 17.72 1.073 -0.0680 19.98 1.006 -0.0680 18.16 1.053 -0.0680 16.76 1.177 -0.0680 14.91 1.176 -0.0680 13.50 1.194 -0.0680 12.15 1.200 -0.0680 10.50 1.194 -0.0680 8.87 1.173 -0.0680 7.32 1.084 -0.0680 6.01 0.973 -0.0680 3.98 0.770 -0.0680 2.40 0.601 -0.0680 1.05 0.458 -0.0680 -0.39 0.304 -0.0680 -1.79 0.169 -0.0680 -3.14 0.046 -0.0680 -5.05 -0.127 -0.0680 Tabulated from data in file AB00145.DAT & reduced using program Q01.00L File s7055.lft created on 12-05-1997 at 15:25:51 using program FORMAT :::::::::::::: S822.LFT :::::::::::::: Airfoil: S822 Builder: M. Allen Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 102500 Number of angles of attack: 33 alpha / Cl / Cm -6.35 -0.579 -0.0700 -4.34 -0.364 -0.0700 -2.81 -0.253 -0.0700 -1.45 -0.197 -0.0700 0.12 -0.105 -0.0700 1.58 0.040 -0.0700 3.15 0.190 -0.0700 4.68 0.353 -0.0700 6.33 0.736 -0.0700 7.94 0.970 -0.0700 9.50 1.074 -0.0700 10.92 1.085 -0.0700 12.42 1.128 -0.0700 13.87 1.155 -0.0700 15.35 0.879 -0.0700 16.75 0.803 -0.0700 18.32 0.807 -0.0700 16.53 0.774 -0.0700 15.19 0.901 -0.0700 13.73 1.146 -0.0700 12.20 1.115 -0.0700 10.68 1.071 -0.0700 9.19 1.043 -0.0700 7.58 0.923 -0.0700 6.07 0.633 -0.0700 4.45 0.305 -0.0700 3.03 0.156 -0.0700 1.36 0.014 -0.0700 -0.11 -0.129 -0.0700 -1.69 -0.210 -0.0700 -3.11 -0.280 -0.0700 -4.68 -0.398 -0.0700 -6.29 -0.585 -0.0700 Tabulated from data in file JG00415.DAT & reduced using program Q01.00L Average Reynolds #: 204300 Number of angles of attack: 33 alpha / Cl / Cm -6.00 -0.356 -0.0700 -4.53 -0.218 -0.0700 -3.14 -0.089 -0.0700 -1.50 0.066 -0.0700 0.05 0.206 -0.0700 1.58 0.351 -0.0700 3.00 0.493 -0.0700 4.63 0.660 -0.0700 6.11 0.832 -0.0700 7.72 0.963 -0.0700 9.06 1.033 -0.0700 10.62 1.082 -0.0700 12.14 1.120 -0.0700 13.61 1.154 -0.0700 15.18 1.178 -0.0700 16.67 1.173 -0.0700 18.08 0.805 -0.0700 16.70 0.799 -0.0700 15.49 1.182 -0.0700 13.84 1.160 -0.0700 12.26 1.121 -0.0700 10.78 1.083 -0.0700 9.27 1.036 -0.0700 7.82 0.964 -0.0700 6.26 0.842 -0.0700 4.82 0.674 -0.0700 3.23 0.505 -0.0700 1.52 0.332 -0.0700 0.02 0.192 -0.0700 -1.57 0.052 -0.0700 -2.96 -0.078 -0.0700 -4.49 -0.221 -0.0700 -6.12 -0.373 -0.0700 Tabulated from data in file JG00418.DAT & reduced using program Q01.00L Average Reynolds #: 306300 Number of angles of attack: 37 alpha / Cl / Cm -8.05 -0.527 -0.0700 -6.76 -0.414 -0.0700 -5.11 -0.265 -0.0700 -3.66 -0.126 -0.0700 -1.87 0.055 -0.0700 -0.45 0.202 -0.0700 1.21 0.383 -0.0700 2.95 0.571 -0.0700 4.58 0.738 -0.0700 5.95 0.858 -0.0700 7.36 0.942 -0.0700 9.02 1.036 -0.0700 10.38 1.097 -0.0700 12.07 1.153 -0.0700 13.44 1.194 -0.0700 14.73 1.216 -0.0700 16.44 1.222 -0.0700 16.66 0.957 -0.0700 19.48 0.856 -0.0700 17.54 0.836 -0.0700 16.21 1.015 -0.0700 14.80 1.215 -0.0700 13.21 1.185 -0.0700 11.66 1.135 -0.0700 10.14 1.082 -0.0700 8.66 1.009 -0.0700 7.01 0.916 -0.0700 5.51 0.815 -0.0700 3.65 0.639 -0.0700 2.23 0.490 -0.0700 0.73 0.327 -0.0700 -0.90 0.151 -0.0700 -2.21 0.014 -0.0700 -3.99 -0.166 -0.0700 -5.38 -0.299 -0.0700 -7.09 -0.451 -0.0700 -8.69 -0.582 -0.0700 Tabulated from data in file JG00438.DAT & reduced using program Q01.00L Average Reynolds #: 408700 Number of angles of attack: 29 alpha / Cl / Cm -8.22 -0.544 -0.0700 -6.58 -0.396 -0.0700 -5.12 -0.259 -0.0700 -3.54 -0.101 -0.0700 -2.00 0.059 -0.0700 -0.55 0.219 -0.0700 1.12 0.401 -0.0700 2.62 0.563 -0.0700 4.28 0.736 -0.0700 5.84 0.876 -0.0700 7.94 0.974 -0.0700 9.37 1.040 -0.0700 10.78 1.106 -0.0700 12.40 1.160 -0.0700 13.52 1.193 -0.0700 11.61 1.132 -0.0700 10.00 1.072 -0.0700 8.33 0.989 -0.0700 6.90 0.931 -0.0700 4.88 0.789 -0.0700 3.58 0.658 -0.0700 1.77 0.463 -0.0700 0.41 0.315 -0.0700 -1.27 0.131 -0.0700 -2.37 0.012 -0.0700 -3.88 -0.148 -0.0700 -5.36 -0.294 -0.0700 -6.82 -0.430 -0.0700 -8.39 -0.566 -0.0700 Tabulated from data in file JG00434.DAT & reduced using program Q01.00L File s822.lft created on 12-05-1997 at 15:25:50 using program FORMAT :::::::::::::: S823.LFT :::::::::::::: Airfoil: S823 Builder: M. Allen Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 102500 Number of angles of attack: 39 alpha / Cl / Cm -7.86 0.013 -0.1500 -6.20 -0.007 -0.1500 -4.63 -0.030 -0.1500 -3.21 0.032 -0.1500 -1.68 -0.047 -0.1500 -0.10 0.110 -0.1500 1.48 0.281 -0.1500 3.02 0.452 -0.1500 4.39 0.587 -0.1500 6.02 0.763 -0.1500 7.62 0.916 -0.1500 9.20 1.064 -0.1500 10.55 1.157 -0.1500 12.21 1.166 -0.1500 13.68 1.137 -0.1500 15.13 1.124 -0.1500 16.68 1.127 -0.1500 18.05 0.835 -0.1500 19.61 0.830 -0.1500 21.16 0.879 -0.1500 19.34 0.795 -0.1500 17.96 0.841 -0.1500 16.53 1.139 -0.1500 15.06 1.132 -0.1500 13.52 1.146 -0.1500 11.98 1.174 -0.1500 10.55 1.159 -0.1500 9.01 1.040 -0.1500 7.56 0.916 -0.1500 5.94 0.758 -0.1500 4.45 0.603 -0.1500 2.79 0.398 -0.1500 1.34 0.245 -0.1500 -0.19 0.099 -0.1500 -1.70 0.093 -0.1500 -3.24 0.043 -0.1500 -4.79 -0.055 -0.1500 -6.23 0.002 -0.1500 -7.76 0.010 -0.1500 Tabulated from data in file JG00453.DAT & reduced using program Q01.00L Average Reynolds #: 204800 Number of angles of attack: 39 alpha / Cl / Cm -7.50 0.012 -0.1500 -6.19 0.017 -0.1500 -4.59 0.049 -0.1500 -3.16 0.023 -0.1500 -1.64 0.066 -0.1500 0.24 0.268 -0.1500 1.61 0.418 -0.1500 3.00 0.569 -0.1500 4.63 0.740 -0.1500 6.08 0.882 -0.1500 7.62 1.020 -0.1500 9.27 1.147 -0.1500 10.62 1.184 -0.1500 12.24 1.167 -0.1500 13.64 1.159 -0.1500 15.14 1.155 -0.1500 16.81 1.152 -0.1500 18.12 1.151 -0.1500 19.52 0.825 -0.1500 21.02 0.886 -0.1500 19.33 0.837 -0.1500 18.07 1.162 -0.1500 16.53 1.168 -0.1500 14.84 1.153 -0.1500 13.35 1.159 -0.1500 11.94 1.171 -0.1500 10.40 1.184 -0.1500 8.94 1.120 -0.1500 7.34 0.987 -0.1500 5.71 0.838 -0.1500 4.35 0.701 -0.1500 2.65 0.521 -0.1500 0.92 0.330 -0.1500 -0.52 0.175 -0.1500 -2.25 -0.008 -0.1500 -3.54 -0.126 -0.1500 -5.16 -0.255 -0.1500 -4.21 0.072 -0.1500 -8.68 -0.025 -0.1500 Tabulated from data in file JG00456.DAT & reduced using program Q01.00L Average Reynolds #: 306700 Number of angles of attack: 39 alpha / Cl / Cm -7.83 -0.522 -0.1500 -6.40 -0.373 -0.1500 -4.89 -0.243 -0.1500 -3.31 -0.106 -0.1500 -1.82 0.048 -0.1500 -0.23 0.219 -0.1500 1.28 0.389 -0.1500 2.82 0.561 -0.1500 4.41 0.733 -0.1500 5.94 0.889 -0.1500 7.49 1.028 -0.1500 9.17 1.145 -0.1500 10.69 1.176 -0.1500 12.36 1.174 -0.1500 13.83 1.174 -0.1500 15.19 1.173 -0.1500 16.54 1.169 -0.1500 18.15 1.159 -0.1500 19.35 0.895 -0.1500 20.87 0.878 -0.1500 19.46 0.882 -0.1500 18.25 1.158 -0.1500 16.15 1.166 -0.1500 14.84 1.170 -0.1500 13.27 1.173 -0.1500 11.80 1.172 -0.1500 10.17 1.168 -0.1500 8.75 1.119 -0.1500 7.26 1.006 -0.1500 5.83 0.874 -0.1500 4.32 0.722 -0.1500 2.87 0.563 -0.1500 1.25 0.380 -0.1500 -0.18 0.220 -0.1500 -1.74 0.054 -0.1500 -3.28 -0.109 -0.1500 -4.89 -0.259 -0.1500 -6.36 -0.385 -0.1500 -7.96 -0.544 -0.1500 Tabulated from data in file AB00460.DAT & reduced using program Q01.00L Average Reynolds #: 409200 Number of angles of attack: 31 alpha / Cl / Cm -7.84 -0.531 -0.1500 -6.39 -0.390 -0.1500 -4.79 -0.250 -0.1500 -3.29 -0.111 -0.1500 -1.73 0.055 -0.1500 -0.23 0.221 -0.1500 1.36 0.400 -0.1500 2.86 0.569 -0.1500 4.46 0.744 -0.1500 6.00 0.897 -0.1500 7.53 1.032 -0.1500 9.04 1.124 -0.1500 10.61 1.156 -0.1500 12.02 1.160 -0.1500 13.54 1.166 -0.1500 15.04 1.163 -0.1500 13.24 1.165 -0.1500 11.59 1.153 -0.1500 10.00 1.144 -0.1500 8.84 1.113 -0.1500 7.35 1.015 -0.1500 5.81 0.875 -0.1500 4.37 0.730 -0.1500 2.82 0.559 -0.1500 1.27 0.383 -0.1500 -0.23 0.213 -0.1500 -1.82 0.037 -0.1500 -3.33 -0.128 -0.1500 -4.88 -0.269 -0.1500 -6.38 -0.406 -0.1500 -7.95 -0.553 -0.1500 Tabulated from data in file JG00463.DAT & reduced using program Q01.00L File s823.lft created on 12-05-1997 at 15:25:50 using program FORMAT :::::::::::::: SD6060.LFT :::::::::::::: Airfoil: SD6060 Builder: C. Fox Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 61100 Number of angles of attack: 49 alpha / Cl / Cm -5.90 -0.356 -0.0390 -5.35 -0.318 -0.0390 -4.31 -0.256 -0.0390 -3.30 -0.181 -0.0390 -2.29 -0.112 -0.0390 -1.26 -0.022 -0.0390 -0.24 0.117 -0.0390 0.86 0.269 -0.0390 1.80 0.411 -0.0390 2.94 0.537 -0.0390 3.93 0.633 -0.0390 4.88 0.718 -0.0390 5.96 0.812 -0.0390 6.98 0.899 -0.0390 7.97 0.975 -0.0390 9.04 1.031 -0.0390 10.01 1.064 -0.0390 11.07 1.091 -0.0390 12.08 1.097 -0.0390 13.05 1.103 -0.0390 14.05 1.083 -0.0390 15.08 1.054 -0.0390 16.02 1.043 -0.0390 17.10 0.997 -0.0390 18.21 0.968 -0.0390 17.43 0.962 -0.0390 16.37 0.988 -0.0390 15.32 1.030 -0.0390 14.38 1.089 -0.0390 13.41 1.098 -0.0390 12.33 1.087 -0.0390 11.42 1.087 -0.0390 10.44 1.064 -0.0390 9.44 1.033 -0.0390 8.37 0.988 -0.0390 7.42 0.921 -0.0390 6.32 0.830 -0.0390 5.43 0.750 -0.0390 4.27 0.645 -0.0390 3.26 0.553 -0.0390 2.19 0.434 -0.0390 1.20 0.314 -0.0390 0.15 0.171 -0.0390 -0.90 0.016 -0.0390 -1.90 -0.086 -0.0390 -2.87 -0.148 -0.0390 -3.96 -0.238 -0.0390 -4.94 -0.290 -0.0390 -5.94 -0.353 -0.0390 Tabulated from data in file MS00312.DAT & reduced using program Q01.00L Average Reynolds #: 100300 Number of angles of attack: 49 alpha / Cl / Cm -6.08 -0.395 -0.0390 -5.33 -0.352 -0.0390 -4.13 -0.273 -0.0390 -3.26 -0.210 -0.0390 -2.32 -0.105 -0.0390 -1.15 0.082 -0.0390 -0.10 0.213 -0.0390 0.91 0.313 -0.0390 2.01 0.419 -0.0390 2.93 0.494 -0.0390 3.94 0.582 -0.0390 5.02 0.683 -0.0390 6.07 0.782 -0.0390 7.08 0.867 -0.0390 7.99 0.941 -0.0390 9.07 0.985 -0.0390 10.00 1.014 -0.0390 11.20 1.044 -0.0390 12.11 1.051 -0.0390 13.01 1.069 -0.0390 14.07 0.997 -0.0390 15.07 0.921 -0.0390 16.12 0.945 -0.0390 17.05 0.894 -0.0390 18.20 0.893 -0.0390 17.28 0.915 -0.0390 16.37 0.906 -0.0390 15.25 0.935 -0.0390 14.34 0.995 -0.0390 13.37 1.028 -0.0390 12.33 1.055 -0.0390 11.31 1.030 -0.0390 10.30 1.009 -0.0390 9.27 0.978 -0.0390 8.30 0.940 -0.0390 7.34 0.876 -0.0390 6.30 0.787 -0.0390 5.32 0.697 -0.0390 4.12 0.581 -0.0390 3.24 0.505 -0.0390 2.10 0.403 -0.0390 1.14 0.313 -0.0390 0.07 0.210 -0.0390 -0.89 0.094 -0.0390 -1.93 -0.070 -0.0390 -2.97 -0.192 -0.0390 -4.05 -0.278 -0.0390 -5.07 -0.347 -0.0390 -6.04 -0.404 -0.0390 Tabulated from data in file MS00314.DAT & reduced using program Q01.00L Average Reynolds #: 152900 Number of angles of attack: 49 alpha / Cl / Cm -6.05 -0.436 -0.0390 -5.01 -0.370 -0.0390 -4.04 -0.267 -0.0390 -2.87 -0.119 -0.0390 -1.87 -0.030 -0.0390 -0.92 0.042 -0.0390 0.05 0.193 -0.0390 1.19 0.285 -0.0390 2.12 0.375 -0.0390 3.22 0.486 -0.0390 4.34 0.597 -0.0390 5.17 0.681 -0.0390 6.29 0.786 -0.0390 7.40 0.878 -0.0390 8.26 0.937 -0.0390 9.33 0.983 -0.0390 10.34 1.014 -0.0390 11.30 1.025 -0.0390 12.25 1.037 -0.0390 13.34 1.066 -0.0390 14.43 0.995 -0.0390 15.34 0.951 -0.0390 16.50 0.970 -0.0390 17.37 0.952 -0.0390 18.44 0.937 -0.0390 16.89 0.957 -0.0390 16.06 0.910 -0.0390 14.95 0.944 -0.0390 14.05 1.038 -0.0390 13.04 1.065 -0.0390 12.25 1.034 -0.0390 11.21 1.025 -0.0390 10.23 1.009 -0.0390 9.18 0.976 -0.0390 8.17 0.926 -0.0390 7.19 0.856 -0.0390 6.14 0.766 -0.0390 5.12 0.668 -0.0390 4.09 0.565 -0.0390 3.01 0.454 -0.0390 2.05 0.358 -0.0390 0.93 0.255 -0.0390 -0.08 0.173 -0.0390 -1.08 0.015 -0.0390 -2.07 -0.052 -0.0390 -3.07 -0.154 -0.0390 -4.14 -0.289 -0.0390 -5.20 -0.383 -0.0390 -6.21 -0.447 -0.0390 Tabulated from data in file PG00539.DAT & reduced using program Q01.00L Average Reynolds #: 203600 Number of angles of attack: 49 alpha / Cl / Cm -6.18 -0.424 -0.0390 -5.32 -0.355 -0.0390 -4.32 -0.229 -0.0390 -3.15 -0.111 -0.0390 -2.24 -0.048 -0.0390 -1.18 0.038 -0.0390 -0.21 0.125 -0.0390 0.98 0.271 -0.0390 2.02 0.371 -0.0390 2.85 0.455 -0.0390 3.89 0.562 -0.0390 5.01 0.680 -0.0390 5.98 0.775 -0.0390 7.04 0.868 -0.0390 8.01 0.940 -0.0390 9.05 0.993 -0.0390 10.07 1.027 -0.0390 11.16 1.041 -0.0390 12.12 1.067 -0.0390 12.98 1.094 -0.0390 14.05 1.072 -0.0390 15.28 1.038 -0.0390 16.16 0.977 -0.0390 17.26 0.966 -0.0390 18.36 1.004 -0.0390 17.10 0.957 -0.0390 16.08 0.990 -0.0390 15.25 1.058 -0.0390 14.22 1.072 -0.0390 13.33 1.101 -0.0390 12.35 1.079 -0.0390 11.40 1.043 -0.0390 10.39 1.030 -0.0390 9.39 1.004 -0.0390 8.36 0.956 -0.0390 7.25 0.879 -0.0390 6.29 0.795 -0.0390 5.29 0.703 -0.0390 4.18 0.587 -0.0390 3.26 0.492 -0.0390 2.22 0.382 -0.0390 1.08 0.271 -0.0390 0.11 0.160 -0.0390 -0.90 0.052 -0.0390 -1.99 -0.038 -0.0390 -3.03 -0.109 -0.0390 -3.96 -0.196 -0.0390 -4.96 -0.320 -0.0390 -6.02 -0.417 -0.0390 Tabulated from data in file JG00072.DAT & reduced using program Q01.00L Average Reynolds #: 304900 Number of angles of attack: 49 alpha / Cl / Cm -6.13 -0.416 -0.0390 -4.82 -0.284 -0.0390 -4.00 -0.213 -0.0390 -2.83 -0.112 -0.0390 -1.96 -0.038 -0.0390 -0.92 0.050 -0.0390 0.10 0.138 -0.0390 1.20 0.283 -0.0390 2.21 0.386 -0.0390 3.20 0.494 -0.0390 4.19 0.600 -0.0390 5.22 0.704 -0.0390 6.26 0.802 -0.0390 7.31 0.887 -0.0390 8.39 0.958 -0.0390 9.29 1.001 -0.0390 10.30 1.029 -0.0390 11.38 1.044 -0.0390 12.32 1.093 -0.0390 13.25 1.104 -0.0390 14.31 1.106 -0.0390 15.33 1.058 -0.0390 16.30 1.025 -0.0390 17.26 0.996 -0.0390 18.30 0.991 -0.0390 17.04 1.001 -0.0390 16.00 1.028 -0.0390 15.12 1.065 -0.0390 14.15 1.117 -0.0390 13.22 1.110 -0.0390 12.08 1.085 -0.0390 11.08 1.036 -0.0390 10.15 1.022 -0.0390 9.06 0.984 -0.0390 8.05 0.928 -0.0390 7.01 0.853 -0.0390 6.03 0.769 -0.0390 5.04 0.677 -0.0390 3.92 0.562 -0.0390 2.92 0.454 -0.0390 1.89 0.346 -0.0390 0.85 0.223 -0.0390 -0.24 0.095 -0.0390 -1.35 -0.001 -0.0390 -2.29 -0.079 -0.0390 -3.49 -0.179 -0.0390 -4.44 -0.260 -0.0390 -5.38 -0.349 -0.0390 -6.56 -0.462 -0.0390 Tabulated from data in file JG00070.DAT & reduced using program Q01.00L File sd6060.lft created on 12-05-1997 at 15:25:51 using program FORMAT :::::::::::::: SD7003.LFT :::::::::::::: Airfoil: SD7003 Builder: M. Allen Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 61200 Number of angles of attack: 33 alpha / Cl / Cm -6.28 -0.422 -0.0350 -4.82 -0.312 -0.0350 -2.95 -0.167 -0.0350 -1.60 -0.063 -0.0350 -0.07 0.083 -0.0350 1.62 0.326 -0.0350 3.04 0.486 -0.0350 4.64 0.623 -0.0350 6.10 0.749 -0.0350 7.70 0.883 -0.0350 9.14 0.985 -0.0350 10.77 1.029 -0.0350 12.19 0.966 -0.0350 13.51 0.906 -0.0350 15.34 0.867 -0.0350 16.77 0.882 -0.0350 18.31 0.878 -0.0350 16.55 0.888 -0.0350 14.93 0.904 -0.0350 13.59 0.916 -0.0350 12.20 0.955 -0.0350 10.71 1.032 -0.0350 9.03 0.959 -0.0350 7.68 0.865 -0.0350 6.01 0.732 -0.0350 4.52 0.603 -0.0350 3.08 0.477 -0.0350 1.48 0.293 -0.0350 -0.01 0.080 -0.0350 -1.61 -0.073 -0.0350 -3.26 -0.209 -0.0350 -4.63 -0.320 -0.0350 -6.34 -0.463 -0.0350 Tabulated from data in file JG00168.DAT & reduced using program Q01.00L Average Reynolds #: 102200 Number of angles of attack: 33 alpha / Cl / Cm -6.32 -0.465 -0.0350 -4.77 -0.329 -0.0350 -3.19 -0.179 -0.0350 -1.51 -0.045 -0.0350 0.04 0.113 -0.0350 1.35 0.328 -0.0350 3.15 0.491 -0.0350 4.44 0.615 -0.0350 6.22 0.787 -0.0350 7.56 0.903 -0.0350 9.29 1.025 -0.0350 10.59 1.086 -0.0350 12.19 0.968 -0.0350 13.57 0.931 -0.0350 15.17 0.919 -0.0350 16.63 0.950 -0.0350 18.29 0.936 -0.0350 16.49 0.927 -0.0350 14.90 0.954 -0.0350 13.56 0.943 -0.0350 12.04 0.949 -0.0350 10.69 1.086 -0.0350 9.10 1.010 -0.0350 7.71 0.911 -0.0350 5.93 0.758 -0.0350 4.50 0.618 -0.0350 3.07 0.477 -0.0350 1.52 0.340 -0.0350 -0.00 0.101 -0.0350 -1.58 -0.051 -0.0350 -3.23 -0.186 -0.0350 -4.74 -0.324 -0.0350 -6.18 -0.453 -0.0350 Tabulated from data in file JG00170.DAT & reduced using program Q01.00L Average Reynolds #: 203400 Number of angles of attack: 33 alpha / Cl / Cm -6.27 -0.453 -0.0350 -4.67 -0.302 -0.0350 -2.83 -0.124 -0.0350 -1.70 -0.023 -0.0350 0.05 0.169 -0.0350 1.56 0.322 -0.0350 3.10 0.478 -0.0350 4.64 0.635 -0.0350 5.95 0.760 -0.0350 7.53 0.905 -0.0350 9.00 1.019 -0.0350 10.54 1.110 -0.0350 11.87 0.985 -0.0350 14.00 0.981 -0.0350 15.27 0.959 -0.0350 16.68 0.943 -0.0350 18.21 0.922 -0.0350 16.44 0.956 -0.0350 14.90 0.943 -0.0350 13.18 0.965 -0.0350 12.06 0.980 -0.0350 10.53 1.109 -0.0350 9.08 1.023 -0.0350 7.59 0.910 -0.0350 6.09 0.775 -0.0350 4.58 0.628 -0.0350 2.86 0.452 -0.0350 1.38 0.299 -0.0350 -0.15 0.139 -0.0350 -1.65 -0.028 -0.0350 -3.23 -0.171 -0.0350 -4.81 -0.326 -0.0350 -6.27 -0.462 -0.0350 Tabulated from data in file JG00172.DAT & reduced using program Q01.00L Average Reynolds #: 304600 Number of angles of attack: 33 alpha / Cl / Cm -6.34 -0.473 -0.0350 -4.33 -0.277 -0.0350 -3.00 -0.145 -0.0350 -1.71 -0.019 -0.0350 0.28 0.179 -0.0350 1.69 0.328 -0.0350 3.28 0.498 -0.0350 4.67 0.642 -0.0350 6.11 0.783 -0.0350 7.75 0.929 -0.0350 9.04 1.033 -0.0350 10.64 1.131 -0.0350 11.68 1.073 -0.0350 13.03 0.994 -0.0350 15.33 0.965 -0.0350 16.30 0.965 -0.0350 17.79 0.928 -0.0350 16.42 0.971 -0.0350 14.83 0.954 -0.0350 13.47 0.992 -0.0350 11.82 1.051 -0.0350 10.62 1.133 -0.0350 9.19 1.048 -0.0350 7.56 0.916 -0.0350 5.89 0.762 -0.0350 4.37 0.608 -0.0350 2.96 0.459 -0.0350 1.35 0.283 -0.0350 -0.17 0.129 -0.0350 -1.86 -0.047 -0.0350 -3.21 -0.176 -0.0350 -4.82 -0.340 -0.0350 -6.45 -0.491 -0.0350 Tabulated from data in file MS00174.DAT & reduced using program Q01.00L File sd7003.lft created on 12-05-1997 at 15:25:52 using program FORMAT :::::::::::::: SD7032D.LFT :::::::::::::: Airfoil: SD7032 (D) Builder: S. Watson Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 61200 Number of angles of attack: 33 alpha / Cl / Cm -5.47 -0.244 -0.1000 -3.78 -0.094 -0.1000 -2.27 0.050 -0.1000 -0.64 0.255 -0.1000 0.79 0.442 -0.1000 2.44 0.638 -0.1000 4.08 0.803 -0.1000 5.56 0.932 -0.1000 7.15 1.066 -0.1000 8.65 1.172 -0.1000 10.22 1.250 -0.1000 11.56 1.306 -0.1000 13.14 1.321 -0.1000 14.55 1.034 -0.1000 16.06 1.045 -0.1000 17.51 1.084 -0.1000 19.06 1.119 -0.1000 17.39 1.127 -0.1000 15.66 1.072 -0.1000 14.39 1.124 -0.1000 12.68 1.056 -0.1000 11.40 1.295 -0.1000 9.84 1.227 -0.1000 8.41 1.141 -0.1000 6.73 1.012 -0.1000 5.27 0.884 -0.1000 3.72 0.741 -0.1000 2.21 0.588 -0.1000 0.64 0.398 -0.1000 -0.80 0.209 -0.1000 -2.43 0.003 -0.1000 -3.97 -0.138 -0.1000 -5.63 -0.282 -0.1000 Tabulated from data in file JG00234.DAT & reduced using program Q01.00L Average Reynolds #: 101500 Number of angles of attack: 33 alpha / Cl / Cm -5.50 -0.278 -0.1000 -3.60 -0.040 -0.1000 -1.95 0.196 -0.1000 -0.57 0.354 -0.1000 1.05 0.528 -0.1000 2.52 0.668 -0.1000 4.08 0.823 -0.1000 5.48 0.958 -0.1000 7.00 1.096 -0.1000 8.58 1.228 -0.1000 10.21 1.330 -0.1000 11.63 1.358 -0.1000 13.14 1.352 -0.1000 14.55 1.322 -0.1000 16.04 1.041 -0.1000 17.66 1.055 -0.1000 19.26 1.059 -0.1000 17.15 1.062 -0.1000 15.77 1.061 -0.1000 14.32 1.048 -0.1000 12.74 1.359 -0.1000 11.43 1.355 -0.1000 9.89 1.315 -0.1000 8.43 1.216 -0.1000 6.72 1.070 -0.1000 5.21 0.926 -0.1000 3.57 0.765 -0.1000 2.18 0.629 -0.1000 0.52 0.470 -0.1000 -0.90 0.306 -0.1000 -2.53 0.107 -0.1000 -4.01 -0.096 -0.1000 -5.53 -0.275 -0.1000 Tabulated from data in file JG00236.DAT & reduced using program Q01.00L Average Reynolds #: 152300 Number of angles of attack: 33 alpha / Cl / Cm -5.58 -0.242 -0.1000 -3.61 0.029 -0.1000 -1.84 0.235 -0.1000 -0.65 0.337 -0.1000 0.91 0.494 -0.1000 2.58 0.670 -0.1000 4.16 0.833 -0.1000 5.58 0.973 -0.1000 7.15 1.113 -0.1000 8.66 1.240 -0.1000 10.13 1.328 -0.1000 11.62 1.360 -0.1000 13.12 1.359 -0.1000 14.57 1.319 -0.1000 16.05 1.275 -0.1000 17.65 1.087 -0.1000 19.16 1.054 -0.1000 17.19 1.075 -0.1000 15.55 1.057 -0.1000 14.44 1.329 -0.1000 12.89 1.356 -0.1000 11.45 1.354 -0.1000 9.83 1.312 -0.1000 8.31 1.206 -0.1000 6.65 1.062 -0.1000 5.28 0.935 -0.1000 3.74 0.780 -0.1000 2.21 0.621 -0.1000 0.43 0.432 -0.1000 -0.96 0.300 -0.1000 -2.46 0.156 -0.1000 -4.00 -0.034 -0.1000 -5.72 -0.280 -0.1000 Tabulated from data in file PG00542.DAT & reduced using program Q01.00L Average Reynolds #: 202400 Number of angles of attack: 33 alpha / Cl / Cm -5.46 -0.143 -0.1000 -3.80 0.056 -0.1000 -2.05 0.231 -0.1000 -0.56 0.362 -0.1000 0.90 0.513 -0.1000 2.50 0.684 -0.1000 4.04 0.843 -0.1000 5.55 0.990 -0.1000 7.03 1.126 -0.1000 8.54 1.249 -0.1000 10.18 1.337 -0.1000 11.67 1.377 -0.1000 13.08 1.380 -0.1000 14.68 1.350 -0.1000 16.35 1.281 -0.1000 17.19 1.094 -0.1000 18.90 1.073 -0.1000 17.08 1.107 -0.1000 15.68 1.117 -0.1000 14.30 1.352 -0.1000 12.88 1.375 -0.1000 11.29 1.364 -0.1000 9.63 1.309 -0.1000 8.28 1.224 -0.1000 6.72 1.089 -0.1000 5.03 0.930 -0.1000 3.75 0.805 -0.1000 1.94 0.618 -0.1000 0.43 0.459 -0.1000 -1.11 0.313 -0.1000 -2.79 0.147 -0.1000 -4.18 0.005 -0.1000 -5.69 -0.184 -0.1000 Tabulated from data in file JG00238.DAT & reduced using program Q01.00L Average Reynolds #: 303700 Number of angles of attack: 33 alpha / Cl / Cm -5.38 -0.110 -0.1000 -3.88 0.038 -0.1000 -2.42 0.176 -0.1000 -0.88 0.333 -0.1000 0.70 0.487 -0.1000 2.34 0.663 -0.1000 3.75 0.808 -0.1000 5.51 0.982 -0.1000 7.16 1.130 -0.1000 8.83 1.261 -0.1000 10.44 1.347 -0.1000 11.84 1.388 -0.1000 13.16 1.391 -0.1000 14.82 1.351 -0.1000 16.01 1.287 -0.1000 16.80 1.365 -0.1000 19.29 1.071 -0.1000 17.44 1.232 -0.1000 15.97 1.204 -0.1000 14.23 1.351 -0.1000 12.77 1.387 -0.1000 11.40 1.377 -0.1000 9.61 1.303 -0.1000 7.98 1.195 -0.1000 6.47 1.064 -0.1000 4.91 0.919 -0.1000 3.43 0.770 -0.1000 1.96 0.615 -0.1000 0.62 0.472 -0.1000 -0.89 0.326 -0.1000 -2.32 0.180 -0.1000 -3.95 0.027 -0.1000 -5.44 -0.122 -0.1000 Tabulated from data in file JG00240.DAT & reduced using program Q01.00L File sd7032d.lft created on 12-05-1997 at 15:25:52 using program FORMAT :::::::::::::: SD7032E.LFT :::::::::::::: Airfoil: SD7032 (E) Builder: H. Michaelis Comment: clean Number of Reynolds #'s: 1 Average Reynolds #: 203100 Number of angles of attack: 33 alpha / Cl / Cm -5.78 -0.193 -0.1000 -4.25 -0.001 -0.1000 -2.53 0.152 -0.1000 -1.06 0.294 -0.1000 0.70 0.460 -0.1000 1.93 0.588 -0.1000 3.50 0.746 -0.1000 5.19 0.907 -0.1000 6.76 1.049 -0.1000 8.13 1.160 -0.1000 9.77 1.256 -0.1000 11.12 1.310 -0.1000 12.57 1.322 -0.1000 14.28 1.285 -0.1000 15.12 1.058 -0.1000 17.02 1.004 -0.1000 18.50 0.999 -0.1000 16.59 1.008 -0.1000 15.26 1.035 -0.1000 14.02 1.292 -0.1000 12.38 1.320 -0.1000 10.94 1.300 -0.1000 9.34 1.229 -0.1000 7.78 1.123 -0.1000 6.22 0.990 -0.1000 4.68 0.849 -0.1000 3.28 0.713 -0.1000 1.62 0.543 -0.1000 0.10 0.384 -0.1000 -1.45 0.244 -0.1000 -3.20 0.078 -0.1000 -4.90 -0.088 -0.1000 -6.07 -0.261 -0.1000 Tabulated from data in file MS00355.DAT & reduced using program Q01.00L File sd7032e.lft created on 12-05-1997 at 15:25:52 using program FORMAT :::::::::::::: SD7037A.LFT :::::::::::::: Airfoil: SD7037 (A) Builder: H. Michaelis Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 61400 Number of angles of attack: 33 alpha / Cl / Cm -6.81 -0.419 -0.0850 -4.22 -0.234 -0.0850 -3.11 -0.152 -0.0850 -1.76 -0.042 -0.0850 0.01 0.128 -0.0850 1.43 0.329 -0.0850 3.08 0.581 -0.0850 4.55 0.741 -0.0850 6.01 0.869 -0.0850 7.73 1.007 -0.0850 9.11 1.088 -0.0850 10.57 1.154 -0.0850 12.16 1.212 -0.0850 13.72 1.116 -0.0850 15.23 1.012 -0.0850 16.61 1.069 -0.0850 18.22 1.096 -0.0850 16.63 1.081 -0.0850 15.20 1.027 -0.0850 13.81 1.018 -0.0850 12.31 1.196 -0.0850 10.76 1.153 -0.0850 9.29 1.082 -0.0850 7.78 0.997 -0.0850 6.24 0.877 -0.0850 4.66 0.744 -0.0850 3.07 0.584 -0.0850 1.46 0.344 -0.0850 -0.09 0.126 -0.0850 -1.53 -0.013 -0.0850 -3.18 -0.149 -0.0850 -4.57 -0.250 -0.0850 -6.17 -0.368 -0.0850 Tabulated from data in file JG00103.DAT & reduced using program Q01.00L Average Reynolds #: 102000 Number of angles of attack: 33 alpha / Cl / Cm -6.29 -0.402 -0.0850 -4.42 -0.254 -0.0850 -2.84 -0.094 -0.0850 -1.56 0.063 -0.0850 0.22 0.292 -0.0850 1.73 0.481 -0.0850 3.31 0.635 -0.0850 4.76 0.759 -0.0850 6.23 0.887 -0.0850 7.82 1.015 -0.0850 9.27 1.086 -0.0850 10.77 1.162 -0.0850 12.26 1.192 -0.0850 13.70 1.013 -0.0850 15.17 0.962 -0.0850 16.66 0.973 -0.0850 18.42 0.959 -0.0850 16.46 0.991 -0.0850 14.80 0.956 -0.0850 13.47 1.007 -0.0850 12.12 1.178 -0.0850 10.67 1.140 -0.0850 8.90 1.048 -0.0850 7.60 0.979 -0.0850 5.96 0.836 -0.0850 4.44 0.700 -0.0850 2.82 0.557 -0.0850 1.41 0.411 -0.0850 -0.21 0.201 -0.0850 -1.73 0.007 -0.0850 -3.39 -0.189 -0.0850 -4.72 -0.298 -0.0850 -6.39 -0.427 -0.0850 Tabulated from data in file JG00222.DAT & reduced using program Q01.00L Average Reynolds #: 203000 Number of angles of attack: 33 alpha / Cl / Cm -6.29 -0.425 -0.0850 -4.51 -0.186 -0.0850 -2.94 -0.011 -0.0850 -1.31 0.152 -0.0850 0.14 0.294 -0.0850 1.55 0.441 -0.0850 3.20 0.608 -0.0850 4.77 0.755 -0.0850 6.44 0.902 -0.0850 7.84 1.001 -0.0850 9.27 1.088 -0.0850 10.77 1.161 -0.0850 12.31 1.192 -0.0850 13.72 1.041 -0.0850 15.34 0.980 -0.0850 16.68 0.970 -0.0850 18.28 0.964 -0.0850 16.37 0.973 -0.0850 14.76 0.961 -0.0850 13.42 1.093 -0.0850 12.06 1.189 -0.0850 10.58 1.152 -0.0850 8.90 1.061 -0.0850 7.58 0.979 -0.0850 6.00 0.857 -0.0850 4.42 0.713 -0.0850 2.69 0.547 -0.0850 1.36 0.410 -0.0850 -0.36 0.228 -0.0850 -1.90 0.084 -0.0850 -3.32 -0.065 -0.0850 -5.00 -0.262 -0.0850 -6.37 -0.444 -0.0850 Tabulated from data in file AB00224.DAT & reduced using program Q01.00L Average Reynolds #: 304200 Number of angles of attack: 33 alpha / Cl / Cm -6.26 -0.372 -0.0850 -4.64 -0.174 -0.0850 -3.21 -0.034 -0.0850 -1.45 0.127 -0.0850 -0.08 0.267 -0.0850 1.66 0.449 -0.0850 3.27 0.612 -0.0850 5.02 0.779 -0.0850 6.35 0.893 -0.0850 7.96 1.008 -0.0850 9.39 1.104 -0.0850 10.96 1.181 -0.0850 12.36 1.215 -0.0850 13.38 1.152 -0.0850 14.67 1.086 -0.0850 16.58 1.027 -0.0850 17.95 0.978 -0.0850 16.50 1.015 -0.0850 15.08 1.066 -0.0850 13.59 1.169 -0.0850 12.11 1.206 -0.0850 10.59 1.164 -0.0850 8.99 1.076 -0.0850 7.40 0.966 -0.0850 5.87 0.846 -0.0850 4.30 0.705 -0.0850 2.42 0.518 -0.0850 1.28 0.402 -0.0850 -0.41 0.220 -0.0850 -1.75 0.092 -0.0850 -3.41 -0.061 -0.0850 -4.83 -0.199 -0.0850 -6.29 -0.392 -0.0850 Tabulated from data in file AB00226.DAT & reduced using program Q01.00L File sd7037a.lft created on 12-05-1997 at 15:25:52 using program FORMAT :::::::::::::: SD7037B.LFT :::::::::::::: Airfoil: SD7037 (B) Builder: D. Thompson Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 61200 Number of angles of attack: 33 alpha / Cl / Cm -6.01 -0.389 -0.0800 -4.14 -0.243 -0.0800 -2.58 -0.118 -0.0800 -1.02 0.019 -0.0800 0.40 0.175 -0.0800 1.97 0.432 -0.0800 3.71 0.629 -0.0800 5.16 0.757 -0.0800 6.57 0.878 -0.0800 8.37 1.017 -0.0800 9.79 1.110 -0.0800 11.32 1.187 -0.0800 12.83 1.216 -0.0800 14.17 0.967 -0.0800 15.59 1.012 -0.0800 17.38 1.006 -0.0800 18.68 1.020 -0.0800 16.87 1.037 -0.0800 15.43 1.006 -0.0800 13.97 0.952 -0.0800 12.45 0.977 -0.0800 10.95 1.170 -0.0800 9.48 1.087 -0.0800 7.91 0.980 -0.0800 6.44 0.865 -0.0800 4.88 0.729 -0.0800 3.37 0.597 -0.0800 1.76 0.394 -0.0800 0.25 0.154 -0.0800 -1.26 -0.006 -0.0800 -2.84 -0.133 -0.0800 -4.34 -0.249 -0.0800 -5.87 -0.375 -0.0800 Tabulated from data in file PG00580.DAT & reduced using program Q01.00L Average Reynolds #: 101700 Number of angles of attack: 33 alpha / Cl / Cm -5.83 -0.351 -0.0800 -4.20 -0.211 -0.0800 -2.91 -0.102 -0.0800 -1.33 0.077 -0.0800 0.30 0.316 -0.0800 1.82 0.503 -0.0800 3.29 0.642 -0.0800 5.03 0.800 -0.0800 6.33 0.916 -0.0800 8.09 1.067 -0.0800 9.38 1.149 -0.0800 11.06 1.229 -0.0800 12.50 1.244 -0.0800 14.01 0.993 -0.0800 15.50 0.986 -0.0800 16.98 1.041 -0.0800 18.67 0.976 -0.0800 17.14 1.035 -0.0800 15.49 0.988 -0.0800 14.11 1.021 -0.0800 12.65 0.995 -0.0800 11.14 1.242 -0.0800 9.61 1.178 -0.0800 8.15 1.079 -0.0800 6.60 0.951 -0.0800 4.99 0.804 -0.0800 3.49 0.663 -0.0800 2.02 0.526 -0.0800 0.39 0.322 -0.0800 -1.19 0.086 -0.0800 -2.63 -0.068 -0.0800 -4.24 -0.206 -0.0800 -5.70 -0.338 -0.0800 Tabulated from data in file AB00099.DAT & reduced using program Q01.00L Average Reynolds #: 152600 Number of angles of attack: 33 alpha / Cl / Cm -5.70 -0.338 -0.0800 -4.00 -0.182 -0.0800 -2.59 -0.016 -0.0800 -0.85 0.211 -0.0800 0.57 0.359 -0.0800 2.13 0.513 -0.0800 3.72 0.676 -0.0800 5.27 0.826 -0.0800 6.78 0.959 -0.0800 8.18 1.077 -0.0800 9.79 1.184 -0.0800 11.34 1.253 -0.0800 12.65 1.270 -0.0800 14.12 1.238 -0.0800 15.56 1.018 -0.0800 17.45 1.028 -0.0800 19.04 1.015 -0.0800 16.10 1.035 -0.0800 15.36 1.042 -0.0800 13.59 1.039 -0.0800 12.48 1.273 -0.0800 11.04 1.247 -0.0800 9.58 1.173 -0.0800 7.79 1.044 -0.0800 6.41 0.919 -0.0800 4.73 0.765 -0.0800 3.32 0.625 -0.0800 1.57 0.447 -0.0800 0.16 0.306 -0.0800 -1.34 0.138 -0.0800 -2.86 -0.071 -0.0800 -4.58 -0.244 -0.0800 -6.00 -0.384 -0.0800 Tabulated from data in file PG00581.DAT & reduced using program Q01.00L Average Reynolds #: 202900 Number of angles of attack: 33 alpha / Cl / Cm -5.83 -0.375 -0.0800 -4.25 -0.190 -0.0800 -2.76 0.013 -0.0800 -0.97 0.212 -0.0800 0.22 0.327 -0.0800 1.78 0.489 -0.0800 3.48 0.668 -0.0800 5.00 0.821 -0.0800 6.50 0.962 -0.0800 7.95 1.082 -0.0800 9.59 1.197 -0.0800 11.05 1.270 -0.0800 12.47 1.286 -0.0800 14.08 1.235 -0.0800 15.11 1.025 -0.0800 16.78 1.048 -0.0800 18.47 1.041 -0.0800 16.78 1.042 -0.0800 15.41 1.014 -0.0800 14.04 1.058 -0.0800 12.70 1.280 -0.0800 11.16 1.278 -0.0800 9.57 1.196 -0.0800 8.18 1.100 -0.0800 6.54 0.961 -0.0800 4.95 0.811 -0.0800 3.50 0.668 -0.0800 1.82 0.489 -0.0800 0.25 0.328 -0.0800 -1.25 0.179 -0.0800 -2.74 0.006 -0.0800 -4.29 -0.209 -0.0800 -5.89 -0.392 -0.0800 Tabulated from data in file AB00097.DAT & reduced using program Q01.00L Average Reynolds #: 304400 Number of angles of attack: 33 alpha / Cl / Cm -5.90 -0.355 -0.0800 -4.54 -0.177 -0.0800 -2.92 0.012 -0.0800 -1.43 0.161 -0.0800 0.15 0.305 -0.0800 1.92 0.493 -0.0800 3.53 0.664 -0.0800 5.07 0.820 -0.0800 6.63 0.964 -0.0800 8.20 1.092 -0.0800 9.52 1.186 -0.0800 11.22 1.275 -0.0800 12.48 1.277 -0.0800 14.20 1.222 -0.0800 15.55 1.224 -0.0800 16.91 1.082 -0.0800 18.27 1.094 -0.0800 17.01 1.085 -0.0800 15.49 1.176 -0.0800 14.03 1.219 -0.0800 12.63 1.268 -0.0800 11.06 1.268 -0.0800 9.66 1.192 -0.0800 8.08 1.078 -0.0800 6.50 0.946 -0.0800 4.87 0.795 -0.0800 3.24 0.629 -0.0800 1.69 0.462 -0.0800 0.00 0.285 -0.0800 -1.32 0.167 -0.0800 -2.73 0.027 -0.0800 -4.29 -0.157 -0.0800 -5.78 -0.346 -0.0800 Tabulated from data in file AB00095.DAT & reduced using program Q01.00L File sd7037b.lft created on 12-05-1997 at 15:25:52 using program FORMAT :::::::::::::: SD8000.LFT :::::::::::::: Airfoil: SD8000 Builder: R. Wagner/R. Olsen Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 61300 Number of angles of attack: 33 alpha / Cl / Cm -5.51 -0.319 -0.0490 -3.92 -0.190 -0.0490 -2.32 -0.068 -0.0490 -0.85 0.066 -0.0490 0.74 0.230 -0.0490 2.33 0.478 -0.0490 3.95 0.660 -0.0490 5.31 0.768 -0.0490 6.89 0.893 -0.0490 8.38 1.001 -0.0490 9.97 1.095 -0.0490 11.48 1.137 -0.0490 13.05 1.051 -0.0490 14.44 0.965 -0.0490 16.06 0.998 -0.0490 17.37 0.982 -0.0490 19.07 1.012 -0.0490 17.41 0.976 -0.0490 15.88 1.016 -0.0490 14.41 1.004 -0.0490 12.89 1.058 -0.0490 11.41 1.114 -0.0490 9.94 1.083 -0.0490 8.40 0.994 -0.0490 6.83 0.878 -0.0490 5.33 0.759 -0.0490 3.79 0.632 -0.0490 2.28 0.451 -0.0490 0.66 0.204 -0.0490 -0.87 0.040 -0.0490 -2.45 -0.095 -0.0490 -4.00 -0.210 -0.0490 -5.48 -0.333 -0.0490 Tabulated from data in file JG00324.DAT & reduced using program Q01.00L Average Reynolds #: 101800 Number of angles of attack: 33 alpha / Cl / Cm -5.58 -0.346 -0.0490 -3.74 -0.196 -0.0490 -2.19 -0.069 -0.0490 -0.82 0.054 -0.0490 0.77 0.253 -0.0490 2.25 0.490 -0.0490 4.02 0.649 -0.0490 5.46 0.773 -0.0490 7.09 0.909 -0.0490 8.49 1.015 -0.0490 10.03 1.103 -0.0490 11.41 1.107 -0.0490 12.97 0.988 -0.0490 14.46 0.974 -0.0490 15.95 0.938 -0.0490 17.52 0.941 -0.0490 18.97 0.970 -0.0490 17.35 0.954 -0.0490 15.73 0.945 -0.0490 14.33 0.961 -0.0490 12.89 1.007 -0.0490 11.43 1.083 -0.0490 9.89 1.085 -0.0490 8.36 0.993 -0.0490 6.80 0.873 -0.0490 5.34 0.750 -0.0490 3.79 0.613 -0.0490 2.20 0.470 -0.0490 0.66 0.221 -0.0490 -0.82 0.046 -0.0490 -2.46 -0.092 -0.0490 -3.88 -0.207 -0.0490 -5.50 -0.338 -0.0490 Tabulated from data in file JG00326.DAT & reduced using program Q01.00L Average Reynolds #: 202800 Number of angles of attack: 33 alpha / Cl / Cm -5.49 -0.329 -0.0490 -3.90 -0.189 -0.0490 -2.35 -0.043 -0.0490 -0.83 0.156 -0.0490 0.75 0.335 -0.0490 2.27 0.487 -0.0490 3.79 0.635 -0.0490 5.20 0.768 -0.0490 6.74 0.904 -0.0490 8.32 1.028 -0.0490 9.86 1.125 -0.0490 11.42 1.182 -0.0490 12.77 1.076 -0.0490 14.31 1.077 -0.0490 15.70 1.045 -0.0490 17.41 1.060 -0.0490 18.69 0.964 -0.0490 17.35 1.055 -0.0490 16.02 1.053 -0.0490 14.35 1.091 -0.0490 12.99 1.074 -0.0490 11.83 1.186 -0.0490 10.09 1.135 -0.0490 8.47 1.036 -0.0490 6.99 0.921 -0.0490 5.38 0.781 -0.0490 3.85 0.637 -0.0490 2.35 0.490 -0.0490 0.78 0.333 -0.0490 -0.69 0.170 -0.0490 -2.32 -0.051 -0.0490 -3.88 -0.197 -0.0490 -5.44 -0.331 -0.0490 Tabulated from data in file MS00328.DAT & reduced using program Q01.00L Average Reynolds #: 304300 Number of angles of attack: 33 alpha / Cl / Cm -5.28 -0.306 -0.0490 -3.65 -0.147 -0.0490 -2.25 0.028 -0.0490 -0.63 0.201 -0.0490 0.75 0.328 -0.0490 2.55 0.512 -0.0490 4.05 0.658 -0.0490 5.51 0.793 -0.0490 7.20 0.945 -0.0490 8.55 1.054 -0.0490 10.26 1.161 -0.0490 11.52 1.205 -0.0490 12.33 1.141 -0.0490 15.01 1.074 -0.0490 15.83 1.067 -0.0490 17.33 1.036 -0.0490 18.87 0.984 -0.0490 17.42 1.064 -0.0490 15.84 1.035 -0.0490 14.48 1.095 -0.0490 13.03 1.116 -0.0490 11.38 1.199 -0.0490 9.78 1.135 -0.0490 8.19 1.024 -0.0490 6.79 0.908 -0.0490 5.04 0.746 -0.0490 3.63 0.607 -0.0490 2.15 0.461 -0.0490 0.43 0.281 -0.0490 -1.09 0.145 -0.0490 -2.47 -0.016 -0.0490 -4.09 -0.212 -0.0490 -5.87 -0.373 -0.0490 Tabulated from data in file JG00330.DAT & reduced using program Q01.00L File sd8000.lft created on 12-05-1997 at 15:25:52 using program FORMAT :::::::::::::: SD8020.LFT :::::::::::::: Airfoil: SD8020 Builder: R. Wagner/R. Olsen Comment: clean Number of Reynolds #'s: 8 Average Reynolds #: 30500 Number of angles of attack: 97 alpha / Cl / Cm -6.72 -0.627 0.0000 -5.98 -0.598 0.0000 -5.60 -0.560 0.0000 -5.09 -0.518 0.0000 -4.59 -0.482 0.0000 -4.03 -0.423 0.0000 -3.62 -0.365 0.0000 -3.01 -0.226 0.0000 -2.56 -0.161 0.0000 -1.95 -0.106 0.0000 -1.52 -0.076 0.0000 -0.95 -0.051 0.0000 -0.55 -0.035 0.0000 0.08 -0.013 0.0000 0.49 -0.006 0.0000 1.04 0.018 0.0000 1.47 0.036 0.0000 1.97 0.073 0.0000 2.49 0.124 0.0000 2.98 0.220 0.0000 3.54 0.339 0.0000 3.97 0.393 0.0000 4.57 0.447 0.0000 4.98 0.482 0.0000 5.60 0.505 0.0000 6.06 0.549 0.0000 6.64 0.573 0.0000 7.16 0.606 0.0000 7.65 0.633 0.0000 8.23 0.686 0.0000 8.69 0.702 0.0000 9.12 0.734 0.0000 9.67 0.754 0.0000 10.18 0.717 0.0000 10.66 0.751 0.0000 11.09 0.724 0.0000 11.68 0.725 0.0000 12.18 0.725 0.0000 12.68 0.705 0.0000 13.16 0.710 0.0000 13.68 0.712 0.0000 14.27 0.701 0.0000 14.65 0.721 0.0000 15.27 0.718 0.0000 15.71 0.753 0.0000 16.21 0.775 0.0000 16.70 0.795 0.0000 17.28 0.806 0.0000 17.70 0.862 0.0000 17.25 0.781 0.0000 16.83 0.779 0.0000 16.40 0.774 0.0000 15.77 0.743 0.0000 15.25 0.722 0.0000 14.80 0.725 0.0000 14.33 0.719 0.0000 13.78 0.728 0.0000 13.40 0.706 0.0000 12.76 0.708 0.0000 12.35 0.701 0.0000 11.75 0.671 0.0000 11.38 0.665 0.0000 10.80 0.740 0.0000 10.30 0.747 0.0000 9.81 0.751 0.0000 9.38 0.745 0.0000 8.80 0.763 0.0000 8.39 0.743 0.0000 7.80 0.732 0.0000 7.23 0.698 0.0000 6.83 0.676 0.0000 6.37 0.638 0.0000 5.75 0.607 0.0000 5.35 0.571 0.0000 4.73 0.545 0.0000 4.23 0.499 0.0000 3.73 0.450 0.0000 3.28 0.356 0.0000 2.68 0.239 0.0000 2.20 0.159 0.0000 1.66 0.119 0.0000 1.25 0.082 0.0000 0.61 0.068 0.0000 0.25 0.043 0.0000 -0.41 0.033 0.0000 -0.79 -0.003 0.0000 -1.48 -0.026 0.0000 -1.93 -0.066 0.0000 -2.44 -0.090 0.0000 -2.87 -0.147 0.0000 -3.49 -0.317 0.0000 -3.91 -0.407 0.0000 -4.54 -0.453 0.0000 -5.01 -0.490 0.0000 -5.54 -0.525 0.0000 -6.03 -0.586 0.0000 -6.57 -0.628 0.0000 Tabulated from data in file MS00262.DAT & reduced using program Q01.00L Average Reynolds #: 39100 Number of angles of attack: 97 alpha / Cl / Cm -6.70 -0.644 0.0000 -6.14 -0.601 0.0000 -5.64 -0.564 0.0000 -5.18 -0.525 0.0000 -4.63 -0.482 0.0000 -4.11 -0.445 0.0000 -3.63 -0.404 0.0000 -3.07 -0.324 0.0000 -2.57 -0.190 0.0000 -2.00 -0.091 0.0000 -1.58 -0.063 0.0000 -1.06 -0.023 0.0000 -0.53 -0.002 0.0000 0.00 0.013 0.0000 0.43 0.016 0.0000 0.95 0.033 0.0000 1.47 0.065 0.0000 1.98 0.125 0.0000 2.53 0.257 0.0000 3.05 0.355 0.0000 3.56 0.401 0.0000 4.12 0.444 0.0000 4.60 0.474 0.0000 5.09 0.513 0.0000 5.63 0.553 0.0000 6.11 0.592 0.0000 6.64 0.626 0.0000 7.11 0.666 0.0000 7.60 0.695 0.0000 8.20 0.741 0.0000 8.69 0.766 0.0000 9.15 0.792 0.0000 9.68 0.797 0.0000 10.15 0.787 0.0000 10.64 0.782 0.0000 11.17 0.766 0.0000 11.64 0.735 0.0000 12.15 0.729 0.0000 12.63 0.732 0.0000 13.18 0.743 0.0000 13.69 0.755 0.0000 14.23 0.752 0.0000 14.67 0.786 0.0000 15.20 0.772 0.0000 15.67 0.816 0.0000 16.24 0.847 0.0000 16.70 0.832 0.0000 17.27 0.879 0.0000 17.73 0.879 0.0000 17.32 0.868 0.0000 16.75 0.878 0.0000 16.27 0.854 0.0000 15.77 0.839 0.0000 15.28 0.832 0.0000 14.76 0.851 0.0000 14.32 0.836 0.0000 13.77 0.807 0.0000 13.30 0.804 0.0000 12.77 0.797 0.0000 12.38 0.788 0.0000 11.77 0.793 0.0000 11.31 0.841 0.0000 10.76 0.793 0.0000 10.31 0.795 0.0000 9.75 0.782 0.0000 9.35 0.794 0.0000 8.73 0.765 0.0000 8.34 0.728 0.0000 7.75 0.704 0.0000 7.26 0.666 0.0000 6.73 0.638 0.0000 6.35 0.604 0.0000 5.76 0.564 0.0000 5.27 0.525 0.0000 4.73 0.493 0.0000 4.25 0.443 0.0000 3.67 0.375 0.0000 3.19 0.303 0.0000 2.62 0.231 0.0000 2.18 0.180 0.0000 1.58 0.119 0.0000 1.16 0.072 0.0000 0.58 0.047 0.0000 0.16 0.020 0.0000 -0.44 -0.003 0.0000 -0.89 -0.041 0.0000 -1.47 -0.071 0.0000 -1.88 -0.113 0.0000 -2.52 -0.185 0.0000 -2.97 -0.271 0.0000 -3.57 -0.356 0.0000 -3.98 -0.411 0.0000 -4.62 -0.481 0.0000 -5.01 -0.523 0.0000 -5.61 -0.566 0.0000 -6.06 -0.602 0.0000 -6.62 -0.638 0.0000 Tabulated from data in file MS00259.DAT & reduced using program Q01.00L Average Reynolds #: 52400 Number of angles of attack: 97 alpha / Cl / Cm -6.51 -0.600 0.0000 -6.00 -0.575 0.0000 -5.62 -0.543 0.0000 -5.09 -0.505 0.0000 -4.60 -0.459 0.0000 -4.08 -0.384 0.0000 -3.57 -0.338 0.0000 -3.02 -0.281 0.0000 -2.60 -0.230 0.0000 -1.97 -0.113 0.0000 -1.53 -0.058 0.0000 -0.92 -0.011 0.0000 -0.56 -0.002 0.0000 0.05 0.015 0.0000 0.47 0.031 0.0000 1.00 0.066 0.0000 1.52 0.124 0.0000 2.02 0.197 0.0000 2.56 0.262 0.0000 3.10 0.329 0.0000 3.54 0.372 0.0000 4.23 0.439 0.0000 4.58 0.465 0.0000 5.19 0.514 0.0000 5.62 0.552 0.0000 6.18 0.598 0.0000 6.61 0.627 0.0000 7.14 0.667 0.0000 7.65 0.697 0.0000 8.16 0.733 0.0000 8.68 0.760 0.0000 9.11 0.788 0.0000 9.69 0.793 0.0000 10.23 0.785 0.0000 10.68 0.788 0.0000 11.22 0.814 0.0000 11.71 0.810 0.0000 12.21 0.803 0.0000 12.69 0.803 0.0000 13.22 0.805 0.0000 13.69 0.805 0.0000 14.20 0.796 0.0000 14.67 0.838 0.0000 15.29 0.833 0.0000 15.68 0.849 0.0000 16.35 0.906 0.0000 16.69 0.844 0.0000 17.27 0.872 0.0000 17.73 0.919 0.0000 17.43 0.879 0.0000 16.83 0.892 0.0000 16.40 0.809 0.0000 15.82 0.875 0.0000 15.30 0.812 0.0000 14.83 0.850 0.0000 14.40 0.825 0.0000 13.83 0.814 0.0000 13.41 0.832 0.0000 12.84 0.789 0.0000 12.37 0.785 0.0000 11.79 0.787 0.0000 11.30 0.810 0.0000 10.83 0.844 0.0000 10.40 0.857 0.0000 9.84 0.848 0.0000 9.45 0.845 0.0000 8.81 0.813 0.0000 8.26 0.778 0.0000 7.83 0.745 0.0000 7.38 0.718 0.0000 6.82 0.685 0.0000 6.34 0.650 0.0000 5.76 0.606 0.0000 5.20 0.563 0.0000 4.68 0.523 0.0000 4.22 0.487 0.0000 3.71 0.453 0.0000 3.29 0.411 0.0000 2.71 0.358 0.0000 2.27 0.301 0.0000 1.65 0.199 0.0000 1.26 0.122 0.0000 0.62 0.099 0.0000 0.24 0.093 0.0000 -0.39 0.081 0.0000 -0.83 0.058 0.0000 -1.44 0.003 0.0000 -1.81 -0.056 0.0000 -2.48 -0.172 0.0000 -2.88 -0.222 0.0000 -3.53 -0.285 0.0000 -3.93 -0.344 0.0000 -4.53 -0.389 0.0000 -5.04 -0.431 0.0000 -5.55 -0.468 0.0000 -6.01 -0.509 0.0000 -6.61 -0.555 0.0000 Tabulated from data in file MS00260.DAT & reduced using program Q01.00L Average Reynolds #: 60600 Number of angles of attack: 97 alpha / Cl / Cm -6.69 -0.681 0.0000 -6.13 -0.645 0.0000 -5.66 -0.609 0.0000 -5.02 -0.561 0.0000 -4.63 -0.529 0.0000 -4.15 -0.486 0.0000 -3.66 -0.436 0.0000 -3.03 -0.373 0.0000 -2.60 -0.319 0.0000 -2.01 -0.230 0.0000 -1.61 -0.146 0.0000 -1.04 -0.079 0.0000 -0.56 -0.056 0.0000 0.05 -0.036 0.0000 0.44 -0.032 0.0000 1.02 0.005 0.0000 1.43 0.073 0.0000 2.10 0.182 0.0000 2.54 0.238 0.0000 3.07 0.289 0.0000 3.56 0.325 0.0000 4.03 0.367 0.0000 4.55 0.405 0.0000 5.13 0.455 0.0000 5.57 0.493 0.0000 6.14 0.539 0.0000 6.63 0.574 0.0000 7.10 0.606 0.0000 7.60 0.640 0.0000 8.10 0.677 0.0000 8.61 0.708 0.0000 9.17 0.738 0.0000 9.67 0.754 0.0000 10.17 0.752 0.0000 10.68 0.766 0.0000 11.22 0.769 0.0000 11.66 0.742 0.0000 12.21 0.744 0.0000 12.67 0.713 0.0000 13.23 0.733 0.0000 13.69 0.772 0.0000 14.27 0.761 0.0000 14.70 0.778 0.0000 15.20 0.837 0.0000 15.64 0.767 0.0000 16.22 0.799 0.0000 16.68 0.829 0.0000 17.25 0.851 0.0000 17.70 0.823 0.0000 17.34 0.855 0.0000 16.73 0.850 0.0000 16.31 0.796 0.0000 15.78 0.818 0.0000 15.31 0.790 0.0000 14.77 0.796 0.0000 14.28 0.765 0.0000 13.75 0.715 0.0000 13.30 0.751 0.0000 12.75 0.730 0.0000 12.23 0.734 0.0000 11.73 0.767 0.0000 11.30 0.772 0.0000 10.76 0.790 0.0000 10.31 0.779 0.0000 9.75 0.762 0.0000 9.33 0.759 0.0000 8.75 0.735 0.0000 8.28 0.706 0.0000 7.75 0.671 0.0000 7.31 0.639 0.0000 6.70 0.595 0.0000 6.32 0.565 0.0000 5.72 0.519 0.0000 5.23 0.480 0.0000 4.68 0.437 0.0000 4.25 0.400 0.0000 3.65 0.352 0.0000 3.22 0.304 0.0000 2.60 0.243 0.0000 2.18 0.194 0.0000 1.57 0.099 0.0000 1.13 0.002 0.0000 0.53 -0.025 0.0000 0.12 -0.025 0.0000 -0.47 -0.044 0.0000 -0.96 -0.083 0.0000 -1.50 -0.144 0.0000 -1.98 -0.230 0.0000 -2.57 -0.326 0.0000 -2.96 -0.363 0.0000 -3.60 -0.422 0.0000 -4.01 -0.468 0.0000 -4.63 -0.516 0.0000 -5.07 -0.557 0.0000 -5.67 -0.606 0.0000 -6.14 -0.644 0.0000 -6.68 -0.685 0.0000 Tabulated from data in file MS00261.DAT & reduced using program Q01.00L Average Reynolds #: 81100 Number of angles of attack: 97 alpha / Cl / Cm -6.53 -0.641 0.0000 -6.15 -0.621 0.0000 -5.68 -0.583 0.0000 -5.06 -0.529 0.0000 -4.62 -0.494 0.0000 -4.13 -0.458 0.0000 -3.62 -0.409 0.0000 -3.09 -0.355 0.0000 -2.61 -0.317 0.0000 -2.10 -0.234 0.0000 -1.58 -0.161 0.0000 -0.97 -0.049 0.0000 -0.57 -0.014 0.0000 -0.05 -0.001 0.0000 0.45 0.005 0.0000 0.99 0.067 0.0000 1.48 0.142 0.0000 2.09 0.223 0.0000 2.53 0.271 0.0000 3.02 0.305 0.0000 3.57 0.352 0.0000 4.02 0.397 0.0000 4.55 0.440 0.0000 5.11 0.484 0.0000 5.56 0.518 0.0000 6.14 0.564 0.0000 6.64 0.600 0.0000 7.22 0.642 0.0000 7.62 0.670 0.0000 8.12 0.703 0.0000 8.64 0.736 0.0000 9.14 0.763 0.0000 9.63 0.786 0.0000 10.20 0.801 0.0000 10.63 0.785 0.0000 11.17 0.794 0.0000 11.67 0.735 0.0000 12.15 0.763 0.0000 12.66 0.748 0.0000 13.19 0.724 0.0000 13.68 0.740 0.0000 14.18 0.728 0.0000 14.68 0.750 0.0000 15.28 0.825 0.0000 15.70 0.804 0.0000 16.22 0.829 0.0000 16.67 0.837 0.0000 17.27 0.824 0.0000 17.64 0.826 0.0000 17.31 0.836 0.0000 16.75 0.818 0.0000 16.35 0.814 0.0000 15.82 0.803 0.0000 15.31 0.820 0.0000 14.75 0.797 0.0000 14.30 0.764 0.0000 13.74 0.730 0.0000 13.33 0.737 0.0000 12.74 0.752 0.0000 12.28 0.768 0.0000 11.78 0.777 0.0000 11.34 0.766 0.0000 10.77 0.782 0.0000 10.34 0.785 0.0000 9.77 0.789 0.0000 9.39 0.776 0.0000 8.76 0.748 0.0000 8.28 0.721 0.0000 7.77 0.687 0.0000 7.33 0.653 0.0000 6.71 0.612 0.0000 6.27 0.574 0.0000 5.70 0.531 0.0000 5.25 0.494 0.0000 4.70 0.451 0.0000 4.28 0.414 0.0000 3.65 0.365 0.0000 3.25 0.327 0.0000 2.63 0.277 0.0000 2.13 0.232 0.0000 1.61 0.157 0.0000 1.15 0.084 0.0000 0.57 -0.008 0.0000 0.16 -0.008 0.0000 -0.46 -0.019 0.0000 -0.86 -0.044 0.0000 -1.51 -0.156 0.0000 -1.90 -0.228 0.0000 -2.53 -0.301 0.0000 -2.99 -0.334 0.0000 -3.57 -0.402 0.0000 -3.97 -0.434 0.0000 -4.60 -0.487 0.0000 -5.11 -0.526 0.0000 -5.62 -0.567 0.0000 -6.05 -0.606 0.0000 -6.64 -0.651 0.0000 Tabulated from data in file MS00263.DAT & reduced using program Q01.00L Average Reynolds #: 101800 Number of angles of attack: 97 alpha / Cl / Cm -6.56 -0.623 0.0000 -6.03 -0.586 0.0000 -5.66 -0.557 0.0000 -5.07 -0.506 0.0000 -4.61 -0.465 0.0000 -4.05 -0.420 0.0000 -3.57 -0.382 0.0000 -3.03 -0.318 0.0000 -2.59 -0.277 0.0000 -2.01 -0.218 0.0000 -1.57 -0.161 0.0000 -0.97 -0.059 0.0000 -0.52 0.015 0.0000 0.09 0.036 0.0000 0.46 0.038 0.0000 1.13 0.146 0.0000 1.55 0.204 0.0000 2.11 0.260 0.0000 2.56 0.288 0.0000 3.07 0.343 0.0000 3.55 0.381 0.0000 4.09 0.426 0.0000 4.60 0.469 0.0000 5.10 0.512 0.0000 5.64 0.559 0.0000 6.19 0.604 0.0000 6.65 0.635 0.0000 7.17 0.674 0.0000 7.67 0.709 0.0000 8.16 0.741 0.0000 8.74 0.778 0.0000 9.14 0.797 0.0000 9.69 0.823 0.0000 10.10 0.812 0.0000 10.73 0.780 0.0000 11.19 0.788 0.0000 11.67 0.779 0.0000 12.24 0.729 0.0000 12.68 0.743 0.0000 13.27 0.748 0.0000 13.69 0.737 0.0000 14.22 0.759 0.0000 14.68 0.793 0.0000 15.30 0.813 0.0000 15.69 0.816 0.0000 16.37 0.854 0.0000 16.66 0.833 0.0000 17.25 0.837 0.0000 17.70 0.886 0.0000 17.27 0.840 0.0000 16.75 0.866 0.0000 16.41 0.801 0.0000 15.79 0.809 0.0000 15.27 0.775 0.0000 14.82 0.764 0.0000 14.38 0.761 0.0000 13.80 0.748 0.0000 13.36 0.740 0.0000 12.81 0.741 0.0000 12.38 0.742 0.0000 11.70 0.763 0.0000 11.28 0.761 0.0000 10.85 0.799 0.0000 10.40 0.794 0.0000 9.81 0.814 0.0000 9.36 0.798 0.0000 8.78 0.768 0.0000 8.38 0.743 0.0000 7.78 0.703 0.0000 7.27 0.665 0.0000 6.78 0.629 0.0000 6.33 0.596 0.0000 5.70 0.549 0.0000 5.33 0.517 0.0000 4.72 0.465 0.0000 4.32 0.432 0.0000 3.67 0.377 0.0000 3.30 0.347 0.0000 2.65 0.294 0.0000 2.25 0.254 0.0000 1.67 0.207 0.0000 1.27 0.150 0.0000 0.61 0.039 0.0000 0.22 0.008 0.0000 -0.41 0.009 0.0000 -0.80 -0.036 0.0000 -1.42 -0.144 0.0000 -1.82 -0.197 0.0000 -2.48 -0.257 0.0000 -2.90 -0.295 0.0000 -3.54 -0.364 0.0000 -4.04 -0.407 0.0000 -4.55 -0.451 0.0000 -5.06 -0.495 0.0000 -5.56 -0.541 0.0000 -6.00 -0.578 0.0000 -6.57 -0.620 0.0000 Tabulated from data in file MS00264.DAT & reduced using program Q01.00L Average Reynolds #: 204200 Number of angles of attack: 33 alpha / Cl / Cm -6.54 -0.637 0.0000 -5.02 -0.504 0.0000 -3.46 -0.364 0.0000 -1.67 -0.211 0.0000 -0.35 -0.036 0.0000 1.15 0.147 0.0000 2.63 0.292 0.0000 4.27 0.437 0.0000 5.75 0.565 0.0000 7.27 0.692 0.0000 8.86 0.807 0.0000 10.13 0.855 0.0000 11.86 0.833 0.0000 13.51 0.800 0.0000 14.93 0.760 0.0000 16.36 0.772 0.0000 17.84 0.788 0.0000 15.93 0.771 0.0000 14.53 0.750 0.0000 12.93 0.795 0.0000 11.63 0.840 0.0000 10.26 0.860 0.0000 8.71 0.790 0.0000 7.19 0.680 0.0000 5.69 0.558 0.0000 4.09 0.416 0.0000 2.58 0.282 0.0000 0.94 0.109 0.0000 -0.47 -0.058 0.0000 -2.08 -0.256 0.0000 -3.58 -0.384 0.0000 -5.20 -0.531 0.0000 -6.70 -0.656 0.0000 Tabulated from data in file JG00255.DAT & reduced using program Q01.00L Average Reynolds #: 305600 Number of angles of attack: 33 alpha / Cl / Cm -6.79 -0.660 0.0000 -4.82 -0.491 0.0000 -3.24 -0.346 0.0000 -1.79 -0.196 0.0000 -0.25 -0.028 0.0000 1.21 0.112 0.0000 2.65 0.286 0.0000 4.15 0.426 0.0000 5.65 0.560 0.0000 7.23 0.691 0.0000 8.83 0.812 0.0000 10.21 0.882 0.0000 11.61 0.861 0.0000 13.16 0.798 0.0000 14.66 0.777 0.0000 16.10 0.797 0.0000 17.78 0.810 0.0000 15.87 0.781 0.0000 14.46 0.761 0.0000 12.81 0.818 0.0000 11.49 0.855 0.0000 10.24 0.875 0.0000 8.72 0.803 0.0000 7.17 0.684 0.0000 5.64 0.553 0.0000 4.08 0.412 0.0000 2.58 0.275 0.0000 1.06 0.091 0.0000 -0.52 -0.054 0.0000 -2.07 -0.235 0.0000 -3.57 -0.377 0.0000 -5.19 -0.526 0.0000 -6.70 -0.656 0.0000 Tabulated from data in file JG00257.DAT & reduced using program Q01.00L File sd8020.lft created on 12-05-1997 at 15:25:52 using program FORMAT :::::::::::::: SD8020T1.LFT :::::::::::::: Airfoil: SD8020 Builder: R. Wagner/R. Olsen Comment: Zig-Zag trip type "B" @ x/c = 25% (h/c = 0.16%) Number of Reynolds #'s: 6 Average Reynolds #: 30500 Number of angles of attack: 97 alpha / Cl / Cm -6.73 -0.575 0.0000 -6.03 -0.539 0.0000 -5.67 -0.523 0.0000 -5.01 -0.480 0.0000 -4.65 -0.467 0.0000 -4.17 -0.417 0.0000 -3.62 -0.326 0.0000 -3.04 -0.234 0.0000 -2.55 -0.159 0.0000 -2.07 -0.102 0.0000 -1.53 -0.065 0.0000 -0.98 -0.028 0.0000 -0.52 0.001 0.0000 -0.03 0.020 0.0000 0.49 0.034 0.0000 1.06 0.062 0.0000 1.50 0.095 0.0000 2.08 0.133 0.0000 2.54 0.246 0.0000 3.02 0.334 0.0000 3.59 0.435 0.0000 4.22 0.487 0.0000 4.58 0.520 0.0000 5.13 0.560 0.0000 5.65 0.600 0.0000 6.12 0.627 0.0000 6.70 0.674 0.0000 7.16 0.701 0.0000 7.67 0.748 0.0000 8.13 0.769 0.0000 8.73 0.808 0.0000 9.15 0.811 0.0000 9.73 0.839 0.0000 10.23 0.832 0.0000 10.71 0.851 0.0000 11.26 0.803 0.0000 11.71 0.818 0.0000 12.25 0.823 0.0000 12.69 0.822 0.0000 13.30 0.825 0.0000 13.69 0.799 0.0000 14.26 0.814 0.0000 14.69 0.831 0.0000 15.27 0.814 0.0000 15.68 0.790 0.0000 16.30 0.824 0.0000 16.71 0.825 0.0000 17.21 0.827 0.0000 17.67 0.841 0.0000 17.26 0.820 0.0000 16.86 0.816 0.0000 16.43 0.815 0.0000 15.80 0.794 0.0000 15.42 0.794 0.0000 14.83 0.770 0.0000 14.38 0.792 0.0000 13.79 0.777 0.0000 13.44 0.782 0.0000 12.82 0.782 0.0000 12.42 0.775 0.0000 11.78 0.793 0.0000 11.42 0.771 0.0000 10.81 0.769 0.0000 10.37 0.745 0.0000 9.85 0.796 0.0000 9.40 0.811 0.0000 8.82 0.794 0.0000 8.30 0.782 0.0000 7.82 0.746 0.0000 7.42 0.716 0.0000 6.80 0.680 0.0000 6.41 0.650 0.0000 5.75 0.604 0.0000 5.21 0.572 0.0000 4.73 0.542 0.0000 4.23 0.512 0.0000 3.74 0.465 0.0000 3.31 0.405 0.0000 2.67 0.301 0.0000 2.18 0.199 0.0000 1.65 0.147 0.0000 1.21 0.124 0.0000 0.64 0.096 0.0000 0.21 0.072 0.0000 -0.39 0.059 0.0000 -0.78 0.038 0.0000 -1.41 0.005 0.0000 -1.81 -0.030 0.0000 -2.44 -0.082 0.0000 -2.80 -0.142 0.0000 -3.49 -0.250 0.0000 -3.89 -0.309 0.0000 -4.49 -0.389 0.0000 -4.94 -0.435 0.0000 -5.49 -0.469 0.0000 -5.96 -0.502 0.0000 -6.50 -0.544 0.0000 Tabulated from data in file MS00271.DAT & reduced using program Q01.00L Average Reynolds #: 40200 Number of angles of attack: 97 alpha / Cl / Cm -6.66 -0.563 0.0000 -5.98 -0.515 0.0000 -5.64 -0.500 0.0000 -5.16 -0.482 0.0000 -4.67 -0.445 0.0000 -4.09 -0.415 0.0000 -3.61 -0.370 0.0000 -3.02 -0.300 0.0000 -2.58 -0.222 0.0000 -2.02 -0.107 0.0000 -1.54 -0.046 0.0000 -0.97 -0.017 0.0000 -0.51 0.007 0.0000 0.03 0.026 0.0000 0.45 0.042 0.0000 1.09 0.065 0.0000 1.48 0.089 0.0000 1.95 0.158 0.0000 2.54 0.286 0.0000 3.17 0.381 0.0000 3.56 0.418 0.0000 4.12 0.468 0.0000 4.59 0.496 0.0000 5.21 0.535 0.0000 5.64 0.570 0.0000 6.15 0.612 0.0000 6.65 0.653 0.0000 7.21 0.688 0.0000 7.69 0.722 0.0000 8.15 0.743 0.0000 8.68 0.767 0.0000 9.12 0.777 0.0000 9.69 0.789 0.0000 10.15 0.802 0.0000 10.71 0.788 0.0000 11.10 0.764 0.0000 11.68 0.764 0.0000 12.23 0.770 0.0000 12.69 0.772 0.0000 13.21 0.760 0.0000 13.67 0.759 0.0000 14.25 0.750 0.0000 14.69 0.764 0.0000 15.18 0.742 0.0000 15.68 0.756 0.0000 16.23 0.740 0.0000 16.64 0.733 0.0000 17.30 0.768 0.0000 17.69 0.763 0.0000 17.34 0.751 0.0000 16.80 0.755 0.0000 16.39 0.733 0.0000 15.87 0.718 0.0000 15.34 0.733 0.0000 14.81 0.744 0.0000 14.38 0.734 0.0000 13.80 0.725 0.0000 13.42 0.745 0.0000 12.79 0.738 0.0000 12.43 0.722 0.0000 11.80 0.724 0.0000 11.36 0.718 0.0000 10.77 0.719 0.0000 10.24 0.758 0.0000 9.81 0.774 0.0000 9.33 0.759 0.0000 8.83 0.756 0.0000 8.30 0.731 0.0000 7.79 0.711 0.0000 7.23 0.677 0.0000 6.79 0.651 0.0000 6.40 0.627 0.0000 5.75 0.584 0.0000 5.36 0.552 0.0000 4.69 0.509 0.0000 4.36 0.489 0.0000 3.71 0.448 0.0000 3.19 0.408 0.0000 2.73 0.356 0.0000 2.28 0.269 0.0000 1.64 0.149 0.0000 1.22 0.084 0.0000 0.64 0.046 0.0000 0.26 0.038 0.0000 -0.41 0.024 0.0000 -0.79 0.004 0.0000 -1.44 -0.040 0.0000 -1.94 -0.091 0.0000 -2.41 -0.168 0.0000 -2.81 -0.241 0.0000 -3.52 -0.343 0.0000 -4.02 -0.385 0.0000 -4.51 -0.429 0.0000 -5.07 -0.480 0.0000 -5.51 -0.508 0.0000 -5.94 -0.538 0.0000 -6.53 -0.579 0.0000 Tabulated from data in file MS00272.DAT & reduced using program Q01.00L Average Reynolds #: 51300 Number of angles of attack: 97 alpha / Cl / Cm -6.71 -0.590 0.0000 -6.16 -0.553 0.0000 -5.73 -0.519 0.0000 -5.14 -0.480 0.0000 -4.66 -0.449 0.0000 -4.11 -0.412 0.0000 -3.70 -0.375 0.0000 -3.08 -0.322 0.0000 -2.65 -0.253 0.0000 -2.13 -0.183 0.0000 -1.61 -0.096 0.0000 -1.10 -0.014 0.0000 -0.58 0.026 0.0000 0.02 0.034 0.0000 0.46 0.045 0.0000 1.02 0.083 0.0000 1.49 0.168 0.0000 2.07 0.250 0.0000 2.51 0.304 0.0000 3.07 0.352 0.0000 3.52 0.412 0.0000 4.07 0.461 0.0000 4.54 0.501 0.0000 5.10 0.547 0.0000 5.55 0.580 0.0000 6.07 0.621 0.0000 6.63 0.665 0.0000 7.12 0.695 0.0000 7.66 0.730 0.0000 8.19 0.763 0.0000 8.64 0.790 0.0000 9.11 0.821 0.0000 9.70 0.847 0.0000 10.20 0.843 0.0000 10.71 0.822 0.0000 11.14 0.826 0.0000 11.68 0.816 0.0000 12.23 0.791 0.0000 12.63 0.820 0.0000 13.18 0.803 0.0000 13.68 0.790 0.0000 14.25 0.804 0.0000 14.64 0.840 0.0000 15.12 0.824 0.0000 15.63 0.807 0.0000 16.12 0.829 0.0000 16.65 0.814 0.0000 17.15 0.816 0.0000 17.66 0.828 0.0000 17.37 0.823 0.0000 16.80 0.801 0.0000 16.31 0.808 0.0000 15.83 0.791 0.0000 15.34 0.794 0.0000 14.79 0.772 0.0000 14.32 0.805 0.0000 13.81 0.804 0.0000 13.33 0.762 0.0000 12.75 0.778 0.0000 12.33 0.752 0.0000 11.79 0.769 0.0000 11.32 0.793 0.0000 10.76 0.780 0.0000 10.35 0.818 0.0000 9.80 0.836 0.0000 9.26 0.817 0.0000 8.76 0.792 0.0000 8.35 0.766 0.0000 7.77 0.730 0.0000 7.28 0.697 0.0000 6.73 0.665 0.0000 6.36 0.633 0.0000 5.72 0.586 0.0000 5.29 0.548 0.0000 4.72 0.501 0.0000 4.26 0.464 0.0000 3.69 0.423 0.0000 3.20 0.367 0.0000 2.65 0.319 0.0000 2.23 0.273 0.0000 1.61 0.174 0.0000 1.26 0.119 0.0000 0.58 0.027 0.0000 0.17 0.020 0.0000 -0.44 0.011 0.0000 -0.84 0.001 0.0000 -1.44 -0.086 0.0000 -1.87 -0.155 0.0000 -2.51 -0.261 0.0000 -2.97 -0.313 0.0000 -3.55 -0.365 0.0000 -3.98 -0.418 0.0000 -4.59 -0.463 0.0000 -5.03 -0.502 0.0000 -5.59 -0.545 0.0000 -6.01 -0.577 0.0000 -6.59 -0.614 0.0000 Tabulated from data in file MS00273.DAT & reduced using program Q01.00L Average Reynolds #: 60600 Number of angles of attack: 97 alpha / Cl / Cm -6.71 -0.616 0.0000 -6.24 -0.586 0.0000 -5.71 -0.549 0.0000 -5.16 -0.504 0.0000 -4.60 -0.461 0.0000 -4.19 -0.429 0.0000 -3.58 -0.380 0.0000 -3.18 -0.342 0.0000 -2.56 -0.269 0.0000 -2.15 -0.215 0.0000 -1.66 -0.135 0.0000 -1.05 -0.037 0.0000 -0.47 0.018 0.0000 0.06 0.030 0.0000 0.49 0.047 0.0000 0.90 0.078 0.0000 1.56 0.189 0.0000 1.97 0.254 0.0000 2.55 0.326 0.0000 3.05 0.365 0.0000 3.57 0.414 0.0000 4.00 0.446 0.0000 4.61 0.495 0.0000 5.04 0.530 0.0000 5.54 0.569 0.0000 6.09 0.610 0.0000 6.59 0.647 0.0000 7.12 0.684 0.0000 7.72 0.728 0.0000 8.14 0.758 0.0000 8.75 0.795 0.0000 9.09 0.818 0.0000 9.61 0.842 0.0000 10.20 0.856 0.0000 10.70 0.839 0.0000 11.09 0.827 0.0000 11.67 0.831 0.0000 12.16 0.817 0.0000 12.72 0.805 0.0000 13.08 0.820 0.0000 13.69 0.804 0.0000 14.22 0.803 0.0000 14.67 0.798 0.0000 15.24 0.830 0.0000 15.68 0.830 0.0000 16.22 0.810 0.0000 16.69 0.823 0.0000 17.14 0.817 0.0000 17.72 0.803 0.0000 17.39 0.826 0.0000 16.83 0.805 0.0000 16.43 0.820 0.0000 15.82 0.828 0.0000 15.43 0.845 0.0000 14.83 0.802 0.0000 14.39 0.807 0.0000 13.83 0.796 0.0000 13.36 0.804 0.0000 12.81 0.782 0.0000 12.41 0.787 0.0000 11.84 0.807 0.0000 11.38 0.813 0.0000 10.81 0.833 0.0000 10.39 0.835 0.0000 9.80 0.832 0.0000 9.36 0.824 0.0000 8.80 0.797 0.0000 8.37 0.773 0.0000 7.77 0.736 0.0000 7.36 0.708 0.0000 6.78 0.667 0.0000 6.39 0.641 0.0000 5.74 0.592 0.0000 5.34 0.559 0.0000 4.69 0.508 0.0000 4.30 0.475 0.0000 3.67 0.422 0.0000 3.28 0.389 0.0000 2.66 0.332 0.0000 2.22 0.287 0.0000 1.62 0.206 0.0000 1.24 0.145 0.0000 0.63 0.052 0.0000 0.22 0.030 0.0000 -0.42 0.022 0.0000 -0.80 0.007 0.0000 -1.43 -0.089 0.0000 -1.81 -0.157 0.0000 -2.46 -0.256 0.0000 -2.91 -0.305 0.0000 -3.51 -0.365 0.0000 -3.93 -0.403 0.0000 -4.56 -0.451 0.0000 -4.96 -0.481 0.0000 -5.54 -0.524 0.0000 -5.93 -0.558 0.0000 -6.57 -0.606 0.0000 Tabulated from data in file MS00274.DAT & reduced using program Q01.00L Average Reynolds #: 80500 Number of angles of attack: 97 alpha / Cl / Cm -6.55 -0.649 0.0000 -6.13 -0.620 0.0000 -5.69 -0.585 0.0000 -5.15 -0.544 0.0000 -4.71 -0.507 0.0000 -4.17 -0.462 0.0000 -3.69 -0.419 0.0000 -3.12 -0.370 0.0000 -2.68 -0.329 0.0000 -2.14 -0.275 0.0000 -1.59 -0.200 0.0000 -1.00 -0.123 0.0000 -0.61 -0.066 0.0000 -0.07 0.010 0.0000 0.45 0.064 0.0000 1.02 0.119 0.0000 1.49 0.174 0.0000 1.97 0.227 0.0000 2.52 0.283 0.0000 3.10 0.336 0.0000 3.54 0.373 0.0000 4.04 0.417 0.0000 4.53 0.457 0.0000 5.11 0.503 0.0000 5.55 0.539 0.0000 6.10 0.585 0.0000 6.57 0.622 0.0000 7.11 0.664 0.0000 7.64 0.699 0.0000 8.16 0.733 0.0000 8.64 0.763 0.0000 9.14 0.793 0.0000 9.63 0.816 0.0000 10.18 0.805 0.0000 10.67 0.795 0.0000 11.23 0.796 0.0000 11.66 0.781 0.0000 12.15 0.767 0.0000 12.64 0.763 0.0000 13.24 0.755 0.0000 13.67 0.776 0.0000 14.16 0.785 0.0000 14.64 0.799 0.0000 15.13 0.753 0.0000 15.62 0.755 0.0000 16.14 0.754 0.0000 16.63 0.775 0.0000 17.16 0.772 0.0000 17.65 0.776 0.0000 17.38 0.760 0.0000 16.81 0.780 0.0000 16.35 0.783 0.0000 15.75 0.750 0.0000 15.39 0.785 0.0000 14.77 0.762 0.0000 14.37 0.773 0.0000 13.81 0.778 0.0000 13.36 0.773 0.0000 12.76 0.753 0.0000 12.31 0.762 0.0000 11.81 0.779 0.0000 11.36 0.775 0.0000 10.77 0.812 0.0000 10.36 0.821 0.0000 9.78 0.814 0.0000 9.32 0.791 0.0000 8.77 0.762 0.0000 8.37 0.738 0.0000 7.75 0.699 0.0000 7.34 0.670 0.0000 6.76 0.627 0.0000 6.31 0.592 0.0000 5.72 0.544 0.0000 5.26 0.506 0.0000 4.69 0.458 0.0000 4.22 0.418 0.0000 3.64 0.370 0.0000 3.24 0.335 0.0000 2.63 0.283 0.0000 2.16 0.233 0.0000 1.64 0.176 0.0000 1.17 0.123 0.0000 0.61 0.061 0.0000 0.16 0.013 0.0000 -0.41 -0.049 0.0000 -0.86 -0.107 0.0000 -1.49 -0.194 0.0000 -1.92 -0.251 0.0000 -2.50 -0.314 0.0000 -2.97 -0.358 0.0000 -3.53 -0.407 0.0000 -3.97 -0.445 0.0000 -4.55 -0.498 0.0000 -4.92 -0.526 0.0000 -5.59 -0.579 0.0000 -5.99 -0.614 0.0000 -6.58 -0.661 0.0000 Tabulated from data in file MS00275.DAT & reduced using program Q01.00L Average Reynolds #: 101400 Number of angles of attack: 97 alpha / Cl / Cm -6.73 -0.641 0.0000 -6.02 -0.591 0.0000 -5.66 -0.562 0.0000 -5.13 -0.514 0.0000 -4.63 -0.472 0.0000 -4.13 -0.429 0.0000 -3.63 -0.384 0.0000 -3.01 -0.329 0.0000 -2.65 -0.296 0.0000 -2.02 -0.238 0.0000 -1.57 -0.189 0.0000 -1.02 -0.129 0.0000 -0.56 -0.057 0.0000 -0.01 0.014 0.0000 0.51 0.089 0.0000 1.01 0.161 0.0000 1.53 0.211 0.0000 2.00 0.255 0.0000 2.53 0.298 0.0000 3.09 0.348 0.0000 3.56 0.390 0.0000 3.99 0.426 0.0000 4.61 0.484 0.0000 5.06 0.522 0.0000 5.64 0.573 0.0000 6.17 0.613 0.0000 6.67 0.651 0.0000 7.17 0.687 0.0000 7.67 0.724 0.0000 8.17 0.757 0.0000 8.67 0.792 0.0000 9.13 0.816 0.0000 9.73 0.846 0.0000 10.17 0.847 0.0000 10.72 0.809 0.0000 11.13 0.804 0.0000 11.65 0.776 0.0000 12.16 0.760 0.0000 12.67 0.777 0.0000 13.27 0.761 0.0000 13.63 0.786 0.0000 14.21 0.788 0.0000 14.65 0.769 0.0000 15.23 0.760 0.0000 15.67 0.766 0.0000 16.17 0.766 0.0000 16.66 0.764 0.0000 17.20 0.771 0.0000 17.70 0.766 0.0000 17.23 0.762 0.0000 16.76 0.772 0.0000 16.35 0.775 0.0000 15.76 0.770 0.0000 15.20 0.758 0.0000 14.76 0.780 0.0000 14.30 0.785 0.0000 13.78 0.783 0.0000 13.36 0.767 0.0000 12.81 0.776 0.0000 12.43 0.766 0.0000 11.86 0.751 0.0000 11.37 0.784 0.0000 10.82 0.794 0.0000 10.40 0.827 0.0000 9.84 0.835 0.0000 9.44 0.812 0.0000 8.81 0.778 0.0000 8.27 0.743 0.0000 7.83 0.712 0.0000 7.41 0.683 0.0000 6.78 0.638 0.0000 6.39 0.608 0.0000 5.72 0.558 0.0000 5.24 0.513 0.0000 4.75 0.471 0.0000 4.35 0.436 0.0000 3.72 0.378 0.0000 3.29 0.341 0.0000 2.70 0.292 0.0000 2.28 0.256 0.0000 1.65 0.203 0.0000 1.23 0.164 0.0000 0.67 0.102 0.0000 0.27 0.042 0.0000 -0.42 -0.047 0.0000 -0.81 -0.102 0.0000 -1.49 -0.190 0.0000 -1.84 -0.225 0.0000 -2.52 -0.285 0.0000 -3.02 -0.326 0.0000 -3.47 -0.367 0.0000 -3.86 -0.402 0.0000 -4.51 -0.458 0.0000 -4.93 -0.498 0.0000 -5.50 -0.550 0.0000 -5.96 -0.590 0.0000 -6.52 -0.633 0.0000 Tabulated from data in file MS00276.DAT & reduced using program Q01.00L File sd8020t1.lft created on 12-05-1997 at 15:25:52 using program FORMAT :::::::::::::: SD8020T2.LFT :::::::::::::: Airfoil: SD8020 Builder: R. Wagner/R. Olsen Comment: Zig-Zag trip type "B" @ x/c = 25% (h/c = 0.32%) Number of Reynolds #'s: 5 Average Reynolds #: 40900 Number of angles of attack: 97 alpha / Cl / Cm -6.70 -0.610 0.0000 -6.07 -0.563 0.0000 -5.68 -0.538 0.0000 -5.21 -0.506 0.0000 -4.68 -0.467 0.0000 -4.13 -0.417 0.0000 -3.68 -0.383 0.0000 -3.05 -0.297 0.0000 -2.64 -0.247 0.0000 -2.08 -0.166 0.0000 -1.61 -0.101 0.0000 -1.07 -0.029 0.0000 -0.58 0.007 0.0000 -0.06 0.047 0.0000 0.43 0.082 0.0000 1.02 0.117 0.0000 1.47 0.175 0.0000 1.97 0.249 0.0000 2.52 0.306 0.0000 3.01 0.351 0.0000 3.55 0.400 0.0000 4.07 0.451 0.0000 4.59 0.492 0.0000 5.11 0.534 0.0000 5.58 0.570 0.0000 6.08 0.607 0.0000 6.60 0.649 0.0000 7.11 0.685 0.0000 7.65 0.717 0.0000 8.14 0.746 0.0000 8.62 0.765 0.0000 9.16 0.790 0.0000 9.68 0.791 0.0000 10.17 0.796 0.0000 10.67 0.778 0.0000 11.13 0.787 0.0000 11.68 0.764 0.0000 12.15 0.800 0.0000 12.70 0.764 0.0000 13.15 0.744 0.0000 13.69 0.753 0.0000 14.18 0.683 0.0000 14.65 0.686 0.0000 15.17 0.696 0.0000 15.63 0.696 0.0000 16.15 0.711 0.0000 16.63 0.721 0.0000 17.14 0.735 0.0000 17.62 0.746 0.0000 17.31 0.753 0.0000 16.78 0.715 0.0000 16.34 0.725 0.0000 15.74 0.717 0.0000 15.30 0.708 0.0000 14.78 0.702 0.0000 14.29 0.713 0.0000 13.79 0.738 0.0000 13.31 0.724 0.0000 12.76 0.756 0.0000 12.29 0.747 0.0000 11.79 0.753 0.0000 11.30 0.789 0.0000 10.76 0.787 0.0000 10.34 0.789 0.0000 9.78 0.777 0.0000 9.35 0.772 0.0000 8.79 0.756 0.0000 8.28 0.726 0.0000 7.76 0.701 0.0000 7.27 0.668 0.0000 6.78 0.637 0.0000 6.30 0.602 0.0000 5.73 0.566 0.0000 5.24 0.527 0.0000 4.69 0.480 0.0000 4.21 0.442 0.0000 3.65 0.391 0.0000 3.26 0.361 0.0000 2.64 0.300 0.0000 2.16 0.251 0.0000 1.64 0.177 0.0000 1.13 0.117 0.0000 0.57 0.073 0.0000 0.15 0.040 0.0000 -0.47 -0.009 0.0000 -0.84 -0.027 0.0000 -1.47 -0.085 0.0000 -1.89 -0.150 0.0000 -2.52 -0.234 0.0000 -2.94 -0.283 0.0000 -3.54 -0.344 0.0000 -3.97 -0.388 0.0000 -4.54 -0.431 0.0000 -5.06 -0.472 0.0000 -5.54 -0.506 0.0000 -6.03 -0.545 0.0000 -6.58 -0.582 0.0000 Tabulated from data in file MS00283.DAT & reduced using program Q01.00L Average Reynolds #: 61000 Number of angles of attack: 97 alpha / Cl / Cm -6.51 -0.585 0.0000 -6.16 -0.561 0.0000 -5.64 -0.525 0.0000 -5.05 -0.479 0.0000 -4.62 -0.444 0.0000 -4.05 -0.397 0.0000 -3.59 -0.359 0.0000 -3.02 -0.313 0.0000 -2.63 -0.276 0.0000 -2.07 -0.222 0.0000 -1.55 -0.162 0.0000 -1.05 -0.100 0.0000 -0.53 -0.031 0.0000 -0.02 0.036 0.0000 0.47 0.098 0.0000 0.95 0.157 0.0000 1.56 0.221 0.0000 1.97 0.261 0.0000 2.57 0.318 0.0000 3.18 0.371 0.0000 3.56 0.405 0.0000 4.17 0.456 0.0000 4.58 0.491 0.0000 5.11 0.534 0.0000 5.60 0.576 0.0000 6.15 0.617 0.0000 6.64 0.647 0.0000 7.04 0.674 0.0000 7.74 0.717 0.0000 8.15 0.743 0.0000 8.73 0.782 0.0000 9.23 0.811 0.0000 9.75 0.830 0.0000 10.13 0.835 0.0000 10.75 0.818 0.0000 11.22 0.809 0.0000 11.68 0.824 0.0000 12.18 0.837 0.0000 12.74 0.774 0.0000 13.14 0.784 0.0000 13.70 0.790 0.0000 14.18 0.789 0.0000 14.75 0.796 0.0000 15.15 0.818 0.0000 15.72 0.783 0.0000 16.16 0.785 0.0000 16.69 0.787 0.0000 17.21 0.771 0.0000 17.72 0.786 0.0000 17.33 0.783 0.0000 16.84 0.788 0.0000 16.43 0.810 0.0000 15.83 0.780 0.0000 15.27 0.770 0.0000 14.83 0.782 0.0000 14.36 0.790 0.0000 13.85 0.803 0.0000 13.35 0.782 0.0000 12.82 0.786 0.0000 12.36 0.769 0.0000 11.82 0.814 0.0000 11.41 0.830 0.0000 10.82 0.823 0.0000 10.42 0.836 0.0000 9.81 0.814 0.0000 9.39 0.795 0.0000 8.82 0.766 0.0000 8.35 0.734 0.0000 7.83 0.700 0.0000 7.37 0.669 0.0000 6.80 0.632 0.0000 6.35 0.603 0.0000 5.75 0.555 0.0000 5.23 0.514 0.0000 4.74 0.473 0.0000 4.28 0.436 0.0000 3.70 0.387 0.0000 3.29 0.351 0.0000 2.70 0.301 0.0000 2.21 0.258 0.0000 1.63 0.206 0.0000 1.26 0.168 0.0000 0.59 0.092 0.0000 0.17 0.038 0.0000 -0.40 -0.039 0.0000 -0.86 -0.103 0.0000 -1.46 -0.175 0.0000 -1.86 -0.220 0.0000 -2.50 -0.277 0.0000 -2.89 -0.309 0.0000 -3.53 -0.368 0.0000 -4.01 -0.408 0.0000 -4.50 -0.449 0.0000 -4.94 -0.484 0.0000 -5.54 -0.534 0.0000 -5.97 -0.564 0.0000 -6.57 -0.608 0.0000 Tabulated from data in file MS00284.DAT & reduced using program Q01.00L Average Reynolds #: 81600 Number of angles of attack: 97 alpha / Cl / Cm -6.72 -0.621 0.0000 -6.16 -0.580 0.0000 -5.64 -0.538 0.0000 -5.12 -0.493 0.0000 -4.70 -0.461 0.0000 -4.22 -0.418 0.0000 -3.58 -0.357 0.0000 -3.11 -0.305 0.0000 -2.56 -0.248 0.0000 -2.15 -0.203 0.0000 -1.58 -0.144 0.0000 -1.15 -0.098 0.0000 -0.61 -0.047 0.0000 0.00 0.010 0.0000 0.50 0.056 0.0000 0.98 0.104 0.0000 1.51 0.157 0.0000 1.95 0.200 0.0000 2.56 0.262 0.0000 3.02 0.310 0.0000 3.59 0.369 0.0000 4.09 0.416 0.0000 4.61 0.464 0.0000 5.04 0.499 0.0000 5.53 0.543 0.0000 6.10 0.591 0.0000 6.68 0.632 0.0000 7.09 0.660 0.0000 7.61 0.694 0.0000 8.08 0.728 0.0000 8.76 0.769 0.0000 9.14 0.789 0.0000 9.61 0.813 0.0000 10.11 0.811 0.0000 10.64 0.799 0.0000 11.12 0.810 0.0000 11.73 0.782 0.0000 12.13 0.775 0.0000 12.73 0.753 0.0000 13.10 0.751 0.0000 13.68 0.732 0.0000 14.15 0.757 0.0000 14.67 0.753 0.0000 15.17 0.755 0.0000 15.67 0.729 0.0000 16.14 0.758 0.0000 16.72 0.744 0.0000 17.12 0.745 0.0000 17.74 0.749 0.0000 17.39 0.749 0.0000 16.79 0.762 0.0000 16.36 0.756 0.0000 15.81 0.763 0.0000 15.38 0.776 0.0000 14.80 0.745 0.0000 14.35 0.773 0.0000 13.81 0.763 0.0000 13.37 0.757 0.0000 12.78 0.770 0.0000 12.40 0.762 0.0000 11.82 0.783 0.0000 11.34 0.781 0.0000 10.79 0.809 0.0000 10.35 0.806 0.0000 9.77 0.796 0.0000 9.35 0.777 0.0000 8.82 0.749 0.0000 8.37 0.719 0.0000 7.76 0.681 0.0000 7.39 0.652 0.0000 6.71 0.604 0.0000 6.36 0.577 0.0000 5.70 0.526 0.0000 5.35 0.494 0.0000 4.69 0.439 0.0000 4.28 0.401 0.0000 3.68 0.345 0.0000 3.20 0.297 0.0000 2.67 0.240 0.0000 2.22 0.196 0.0000 1.60 0.131 0.0000 1.15 0.083 0.0000 0.56 0.027 0.0000 0.18 -0.005 0.0000 -0.41 -0.058 0.0000 -0.84 -0.098 0.0000 -1.53 -0.167 0.0000 -1.89 -0.206 0.0000 -2.49 -0.268 0.0000 -2.90 -0.308 0.0000 -3.52 -0.372 0.0000 -3.97 -0.419 0.0000 -4.53 -0.467 0.0000 -4.99 -0.505 0.0000 -5.51 -0.547 0.0000 -6.00 -0.590 0.0000 -6.54 -0.632 0.0000 Tabulated from data in file MS00285.DAT & reduced using program Q01.00L Average Reynolds #: 101600 Number of angles of attack: 97 alpha / Cl / Cm -6.53 -0.613 0.0000 -6.16 -0.588 0.0000 -5.66 -0.548 0.0000 -5.08 -0.497 0.0000 -4.63 -0.453 0.0000 -4.10 -0.403 0.0000 -3.64 -0.359 0.0000 -3.19 -0.308 0.0000 -2.56 -0.247 0.0000 -1.99 -0.189 0.0000 -1.56 -0.145 0.0000 -1.03 -0.091 0.0000 -0.52 -0.043 0.0000 -0.09 -0.005 0.0000 0.50 0.048 0.0000 0.89 0.082 0.0000 1.53 0.146 0.0000 1.99 0.192 0.0000 2.53 0.245 0.0000 3.09 0.306 0.0000 3.58 0.355 0.0000 4.00 0.395 0.0000 4.58 0.447 0.0000 5.13 0.501 0.0000 5.61 0.544 0.0000 6.02 0.576 0.0000 6.63 0.622 0.0000 7.07 0.655 0.0000 7.69 0.698 0.0000 8.18 0.729 0.0000 8.75 0.766 0.0000 9.20 0.793 0.0000 9.68 0.817 0.0000 10.19 0.814 0.0000 10.69 0.803 0.0000 11.16 0.788 0.0000 11.75 0.781 0.0000 12.07 0.746 0.0000 12.63 0.748 0.0000 13.18 0.724 0.0000 13.72 0.752 0.0000 14.18 0.741 0.0000 14.70 0.754 0.0000 15.21 0.753 0.0000 15.73 0.760 0.0000 16.24 0.748 0.0000 16.67 0.732 0.0000 17.19 0.742 0.0000 17.67 0.752 0.0000 17.25 0.738 0.0000 16.73 0.740 0.0000 16.46 0.747 0.0000 15.83 0.747 0.0000 15.25 0.758 0.0000 14.86 0.759 0.0000 14.40 0.738 0.0000 13.85 0.758 0.0000 13.43 0.735 0.0000 12.75 0.742 0.0000 12.26 0.743 0.0000 11.85 0.765 0.0000 11.44 0.754 0.0000 10.82 0.799 0.0000 10.37 0.806 0.0000 9.85 0.813 0.0000 9.40 0.786 0.0000 8.82 0.754 0.0000 8.35 0.724 0.0000 7.77 0.685 0.0000 7.22 0.646 0.0000 6.78 0.615 0.0000 6.22 0.574 0.0000 5.73 0.538 0.0000 5.37 0.504 0.0000 4.72 0.444 0.0000 4.28 0.400 0.0000 3.69 0.344 0.0000 3.26 0.301 0.0000 2.66 0.237 0.0000 2.24 0.194 0.0000 1.66 0.135 0.0000 1.27 0.098 0.0000 0.58 0.030 0.0000 0.17 -0.004 0.0000 -0.42 -0.056 0.0000 -0.84 -0.089 0.0000 -1.42 -0.149 0.0000 -1.80 -0.182 0.0000 -2.46 -0.248 0.0000 -2.87 -0.287 0.0000 -3.51 -0.352 0.0000 -4.02 -0.404 0.0000 -4.48 -0.447 0.0000 -5.03 -0.497 0.0000 -5.57 -0.547 0.0000 -5.90 -0.575 0.0000 -6.53 -0.622 0.0000 Tabulated from data in file MS00286.DAT & reduced using program Q01.00L Average Reynolds #: 205000 Number of angles of attack: 10 alpha / Cl / Cm -6.54 -0.633 0.0000 -4.64 -0.465 0.0000 -2.66 -0.264 0.0000 -0.56 -0.063 0.0000 1.50 0.125 0.0000 3.59 0.342 0.0000 5.67 0.536 0.0000 6.70 0.624 0.0000 7.72 0.706 0.0000 8.78 0.779 0.0000 Tabulated from data in file MS00288.DAT & reduced using program Q01.00L File sd8020t2.lft created on 12-05-1997 at 15:25:52 using program FORMAT :::::::::::::: WASP.LFT :::::::::::::: Airfoil: WASP Builder: M. Fox Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 61100 Number of angles of attack: 33 alpha / Cl / Cm -5.89 -0.302 -0.0740 -4.26 -0.189 -0.0740 -2.66 -0.065 -0.0740 -1.05 0.081 -0.0740 0.33 0.281 -0.0740 1.95 0.515 -0.0740 3.38 0.640 -0.0740 4.97 0.778 -0.0740 6.62 0.915 -0.0740 8.12 1.029 -0.0740 9.60 1.140 -0.0740 11.21 1.214 -0.0740 12.58 1.227 -0.0740 14.05 1.037 -0.0740 15.68 1.003 -0.0740 17.15 1.023 -0.0740 18.56 1.025 -0.0740 16.87 1.035 -0.0740 15.47 1.093 -0.0740 13.98 1.071 -0.0740 12.56 1.254 -0.0740 10.98 1.229 -0.0740 9.50 1.153 -0.0740 7.91 1.037 -0.0740 6.41 0.919 -0.0740 4.79 0.790 -0.0740 3.37 0.668 -0.0740 1.76 0.520 -0.0740 0.32 0.300 -0.0740 -1.30 0.077 -0.0740 -2.80 -0.053 -0.0740 -4.35 -0.170 -0.0740 -5.84 -0.283 -0.0740 Tabulated from data in file AB00228.DAT & reduced using program Q01.00L Average Reynolds #: 101900 Number of angles of attack: 33 alpha / Cl / Cm -5.92 -0.339 -0.0740 -4.18 -0.199 -0.0740 -2.44 -0.052 -0.0740 -0.86 0.154 -0.0740 0.32 0.345 -0.0740 2.04 0.516 -0.0740 3.65 0.662 -0.0740 5.26 0.815 -0.0740 7.06 0.972 -0.0740 8.27 1.077 -0.0740 9.91 1.194 -0.0740 11.52 1.239 -0.0740 12.59 1.243 -0.0740 14.15 1.219 -0.0740 15.50 1.042 -0.0740 17.21 0.987 -0.0740 19.03 1.019 -0.0740 16.19 1.007 -0.0740 15.16 0.984 -0.0740 13.92 1.204 -0.0740 12.33 1.221 -0.0740 10.67 1.208 -0.0740 9.36 1.144 -0.0740 7.78 1.016 -0.0740 6.49 0.903 -0.0740 4.72 0.738 -0.0740 3.27 0.603 -0.0740 1.53 0.447 -0.0740 0.07 0.279 -0.0740 -1.26 0.074 -0.0740 -3.10 -0.132 -0.0740 -4.40 -0.228 -0.0740 -6.21 -0.380 -0.0740 Tabulated from data in file AB00143.DAT & reduced using program Q01.00L Average Reynolds #: 203200 Number of angles of attack: 33 alpha / Cl / Cm -5.90 -0.350 -0.0740 -4.10 -0.175 -0.0740 -2.62 0.018 -0.0740 -0.85 0.222 -0.0740 0.37 0.349 -0.0740 2.17 0.534 -0.0740 3.48 0.661 -0.0740 5.16 0.827 -0.0740 6.60 0.961 -0.0740 8.24 1.100 -0.0740 9.76 1.197 -0.0740 11.06 1.229 -0.0740 12.51 1.223 -0.0740 14.27 1.206 -0.0740 15.43 1.101 -0.0740 17.19 0.943 -0.0740 18.80 0.938 -0.0740 16.77 0.961 -0.0740 15.15 1.140 -0.0740 14.00 1.194 -0.0740 12.50 1.219 -0.0740 11.05 1.226 -0.0740 9.51 1.178 -0.0740 7.98 1.070 -0.0740 6.38 0.930 -0.0740 4.77 0.779 -0.0740 3.21 0.623 -0.0740 1.82 0.484 -0.0740 0.19 0.317 -0.0740 -1.45 0.152 -0.0740 -2.98 -0.042 -0.0740 -4.57 -0.237 -0.0740 -5.98 -0.370 -0.0740 Tabulated from data in file AB00230.DAT & reduced using program Q01.00L Average Reynolds #: 304100 Number of angles of attack: 33 alpha / Cl / Cm -5.97 -0.352 -0.0740 -4.26 -0.164 -0.0740 -2.55 0.042 -0.0740 -1.09 0.187 -0.0740 0.82 0.386 -0.0740 2.13 0.520 -0.0740 3.48 0.658 -0.0740 5.11 0.817 -0.0740 6.56 0.953 -0.0740 8.17 1.091 -0.0740 9.57 1.186 -0.0740 11.30 1.235 -0.0740 12.61 1.228 -0.0740 14.19 1.214 -0.0740 15.64 1.170 -0.0740 16.90 0.979 -0.0740 18.39 0.988 -0.0740 16.91 1.003 -0.0740 15.40 1.203 -0.0740 13.97 1.214 -0.0740 12.51 1.227 -0.0740 11.02 1.231 -0.0740 9.42 1.179 -0.0740 7.93 1.072 -0.0740 6.30 0.929 -0.0740 4.75 0.776 -0.0740 3.23 0.626 -0.0740 1.66 0.465 -0.0740 -0.16 0.280 -0.0740 -1.51 0.141 -0.0740 -3.18 -0.027 -0.0740 -4.75 -0.224 -0.0740 -6.18 -0.382 -0.0740 Tabulated from data in file AB00232.DAT & reduced using program Q01.00L File wasp.lft created on 12-05-1997 at 15:25:53 using program FORMAT