Moment data in this file is meaningless. mss 3-20-98 :::::::::::::: 7037B.LFT :::::::::::::: Airfoil: SD7037 (B) Builder: D. Thompson Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60300 Number of angles of attack: 49 alpha / Cl / Cm -5.98 -0.321 -0.0800 -4.49 -0.216 -0.0800 -3.67 -0.161 -0.0800 -2.42 -0.058 -0.0800 -1.49 0.005 -0.0800 -0.59 0.095 -0.0800 0.59 0.223 -0.0800 1.50 0.360 -0.0800 2.73 0.537 -0.0800 3.66 0.629 -0.0800 4.61 0.707 -0.0800 5.85 0.809 -0.0800 6.82 0.889 -0.0800 7.80 0.963 -0.0800 8.76 1.019 -0.0800 9.71 1.076 -0.0800 10.89 1.143 -0.0800 11.79 1.181 -0.0800 12.94 1.199 -0.0800 13.77 0.930 -0.0800 14.72 0.978 -0.0800 15.77 0.957 -0.0800 16.78 0.971 -0.0800 17.78 0.962 -0.0800 18.75 0.955 -0.0800 17.25 0.933 -0.0800 16.28 1.005 -0.0800 15.25 0.967 -0.0800 14.29 0.942 -0.0800 13.30 0.943 -0.0800 12.25 0.970 -0.0800 11.32 1.174 -0.0800 10.37 1.130 -0.0800 9.23 1.056 -0.0800 8.26 1.000 -0.0800 7.25 0.934 -0.0800 6.26 0.854 -0.0800 5.26 0.769 -0.0800 4.26 0.691 -0.0800 3.13 0.587 -0.0800 2.16 0.461 -0.0800 0.99 0.283 -0.0800 0.01 0.144 -0.0800 -0.98 0.058 -0.0800 -1.96 -0.024 -0.0800 -2.94 -0.097 -0.0800 -4.08 -0.191 -0.0800 -5.05 -0.256 -0.0800 -6.01 -0.325 -0.0800 Tabulated from data in file CL00797.DAT & reduced using program Q02.00L Average Reynolds #: 100200 Number of angles of attack: 49 alpha / Cl / Cm -5.95 -0.352 -0.0800 -4.64 -0.225 -0.0800 -3.42 -0.125 -0.0800 -2.52 -0.044 -0.0800 -1.39 0.070 -0.0800 -0.28 0.212 -0.0800 0.63 0.348 -0.0800 1.56 0.465 -0.0800 2.78 0.581 -0.0800 3.73 0.664 -0.0800 4.67 0.748 -0.0800 5.65 0.832 -0.0800 6.92 0.943 -0.0800 7.63 1.008 -0.0800 8.84 1.088 -0.0800 9.79 1.144 -0.0800 10.96 1.206 -0.0800 11.88 1.232 -0.0800 12.78 1.242 -0.0800 13.88 1.219 -0.0800 14.80 0.974 -0.0800 15.89 1.000 -0.0800 16.90 1.020 -0.0800 17.75 0.985 -0.0800 18.74 0.980 -0.0800 17.12 1.005 -0.0800 16.31 1.015 -0.0800 15.26 1.002 -0.0800 14.34 0.996 -0.0800 13.34 0.990 -0.0800 12.19 1.225 -0.0800 11.40 1.207 -0.0800 10.25 1.155 -0.0800 9.30 1.100 -0.0800 8.29 1.039 -0.0800 7.27 0.955 -0.0800 6.23 0.868 -0.0800 5.21 0.779 -0.0800 4.19 0.690 -0.0800 3.18 0.600 -0.0800 2.20 0.511 -0.0800 1.03 0.393 -0.0800 0.01 0.245 -0.0800 -1.01 0.105 -0.0800 -2.04 -0.013 -0.0800 -3.06 -0.102 -0.0800 -4.01 -0.181 -0.0800 -5.01 -0.260 -0.0800 -6.14 -0.367 -0.0800 Tabulated from data in file CL00799.DAT & reduced using program Q02.00L Average Reynolds #: 200600 Number of angles of attack: 49 alpha / Cl / Cm -6.05 -0.299 -0.0800 -4.56 -0.144 -0.0800 -3.54 -0.038 -0.0800 -2.39 0.079 -0.0800 -1.53 0.168 -0.0800 -0.40 0.270 -0.0800 0.71 0.370 -0.0800 1.71 0.467 -0.0800 2.55 0.552 -0.0800 3.66 0.661 -0.0800 4.66 0.771 -0.0800 5.66 0.864 -0.0800 6.78 0.962 -0.0800 7.64 1.034 -0.0800 8.70 1.110 -0.0800 9.76 1.179 -0.0800 10.81 1.234 -0.0800 11.83 1.269 -0.0800 12.81 1.273 -0.0800 13.73 1.251 -0.0800 14.79 1.228 -0.0800 15.58 1.003 -0.0800 16.67 1.018 -0.0800 17.65 1.049 -0.0800 18.61 1.036 -0.0800 17.15 1.017 -0.0800 16.27 1.026 -0.0800 15.23 1.038 -0.0800 14.31 1.049 -0.0800 13.30 1.262 -0.0800 12.43 1.276 -0.0800 11.34 1.250 -0.0800 10.44 1.211 -0.0800 9.41 1.149 -0.0800 8.32 1.073 -0.0800 7.24 0.992 -0.0800 6.31 0.909 -0.0800 5.32 0.817 -0.0800 4.25 0.714 -0.0800 3.09 0.588 -0.0800 2.08 0.487 -0.0800 1.09 0.389 -0.0800 0.04 0.289 -0.0800 -0.94 0.207 -0.0800 -1.90 0.115 -0.0800 -3.14 -0.017 -0.0800 -3.99 -0.104 -0.0800 -4.99 -0.203 -0.0800 -6.06 -0.320 -0.0800 Tabulated from data in file CL00801.DAT & reduced using program Q02.00L Average Reynolds #: 300900 Number of angles of attack: 49 alpha / Cl / Cm -6.03 -0.269 -0.0800 -4.29 -0.096 -0.0800 -3.40 -0.013 -0.0800 -2.59 0.065 -0.0800 -1.28 0.177 -0.0800 -0.37 0.263 -0.0800 0.82 0.391 -0.0800 1.48 0.457 -0.0800 2.61 0.573 -0.0800 3.64 0.676 -0.0800 4.75 0.785 -0.0800 5.81 0.885 -0.0800 6.65 0.957 -0.0800 7.78 1.050 -0.0800 8.63 1.115 -0.0800 9.68 1.191 -0.0800 10.69 1.254 -0.0800 11.85 1.296 -0.0800 12.79 1.299 -0.0800 13.68 1.280 -0.0800 14.70 1.251 -0.0800 15.37 1.123 -0.0800 16.68 1.091 -0.0800 17.60 1.082 -0.0800 18.77 1.046 -0.0800 17.20 1.103 -0.0800 16.18 1.083 -0.0800 15.18 1.087 -0.0800 14.71 1.252 -0.0800 13.30 1.287 -0.0800 12.42 1.300 -0.0800 11.35 1.278 -0.0800 10.37 1.231 -0.0800 9.22 1.157 -0.0800 8.22 1.081 -0.0800 7.14 0.997 -0.0800 6.24 0.918 -0.0800 5.16 0.819 -0.0800 4.08 0.715 -0.0800 2.97 0.604 -0.0800 2.06 0.511 -0.0800 1.00 0.402 -0.0800 -0.03 0.287 -0.0800 -1.05 0.196 -0.0800 -2.16 0.100 -0.0800 -3.16 0.005 -0.0800 -4.18 -0.091 -0.0800 -5.08 -0.176 -0.0800 -6.10 -0.278 -0.0800 Tabulated from data in file CL00803.DAT & reduced using program Q02.00L File 7037b.lft created on 09-12-1997 at 13:46:18 using program FORMAT :::::::::::::: 7037BF10.LFT :::::::::::::: Airfoil: SD7037 (B) Builder: D. Thompson Comment: clean: flap = 10 degs Number of Reynolds #'s: 4 Average Reynolds #: 60000 Number of angles of attack: 49 alpha / Cl / Cm -5.97 -0.115 -0.1200 -4.23 0.058 -0.1200 -3.36 0.133 -0.1200 -2.30 0.217 -0.1200 -1.24 0.320 -0.1200 -0.53 0.389 -0.1200 0.55 0.491 -0.1200 1.65 0.645 -0.1200 2.75 0.830 -0.1200 3.84 0.996 -0.1200 4.95 1.081 -0.1200 5.67 1.126 -0.1200 6.78 1.180 -0.1200 7.91 1.224 -0.1200 9.05 1.273 -0.1200 9.77 1.302 -0.1200 10.85 1.339 -0.1200 11.91 1.341 -0.1200 12.91 1.113 -0.1200 13.85 1.096 -0.1200 14.95 1.090 -0.1200 16.02 1.133 -0.1200 16.73 1.114 -0.1200 17.85 1.111 -0.1200 18.99 1.130 -0.1200 17.10 1.140 -0.1200 16.15 1.093 -0.1200 15.22 1.083 -0.1200 14.04 1.124 -0.1200 13.16 1.115 -0.1200 12.26 1.161 -0.1200 11.09 1.342 -0.1200 10.34 1.332 -0.1200 9.16 1.294 -0.1200 8.25 1.255 -0.1200 7.32 1.220 -0.1200 6.10 1.168 -0.1200 5.14 1.106 -0.1200 4.21 1.041 -0.1200 3.27 0.937 -0.1200 2.04 0.698 -0.1200 1.10 0.586 -0.1200 -0.11 0.444 -0.1200 -1.02 0.367 -0.1200 -1.95 0.271 -0.1200 -3.18 0.180 -0.1200 -4.11 0.098 -0.1200 -5.07 0.009 -0.1200 -5.99 -0.084 -0.1200 Tabulated from data in file CL00814.DAT & reduced using program Q02.00L Average Reynolds #: 100400 Number of angles of attack: 49 alpha / Cl / Cm -5.93 0.001 -0.1200 -4.44 0.113 -0.1200 -3.42 0.215 -0.1200 -2.55 0.291 -0.1200 -1.41 0.385 -0.1200 -0.55 0.467 -0.1200 0.58 0.589 -0.1200 1.74 0.798 -0.1200 2.61 0.922 -0.1200 3.73 1.022 -0.1200 4.87 1.115 -0.1200 5.77 1.180 -0.1200 6.95 1.254 -0.1200 7.85 1.284 -0.1200 8.83 1.320 -0.1200 9.93 1.361 -0.1200 10.81 1.378 -0.1200 11.83 1.388 -0.1200 12.88 1.365 -0.1200 13.74 1.079 -0.1200 14.70 1.104 -0.1200 15.84 1.157 -0.1200 16.84 1.103 -0.1200 17.76 1.149 -0.1200 18.95 1.127 -0.1200 17.14 1.140 -0.1200 16.34 1.106 -0.1200 15.18 1.097 -0.1200 14.37 1.097 -0.1200 13.29 1.109 -0.1200 12.31 1.293 -0.1200 11.37 1.375 -0.1200 10.30 1.358 -0.1200 9.46 1.332 -0.1200 8.37 1.290 -0.1200 7.27 1.251 -0.1200 6.36 1.202 -0.1200 5.20 1.121 -0.1200 4.27 1.047 -0.1200 3.15 0.949 -0.1200 2.23 0.861 -0.1200 1.26 0.692 -0.1200 0.15 0.519 -0.1200 -0.95 0.395 -0.1200 -1.91 0.314 -0.1200 -2.88 0.246 -0.1200 -4.00 0.135 -0.1200 -4.94 0.044 -0.1200 -6.00 -0.043 -0.1200 Tabulated from data in file CL00816.DAT & reduced using program Q02.00L Average Reynolds #: 200100 Number of angles of attack: 49 alpha / Cl / Cm -6.00 0.099 -0.1200 -4.34 0.256 -0.1200 -3.32 0.346 -0.1200 -2.33 0.447 -0.1200 -1.34 0.540 -0.1200 -0.37 0.585 -0.1200 0.47 0.717 -0.1200 1.74 0.864 -0.1200 2.73 0.946 -0.1200 3.70 1.027 -0.1200 4.66 1.103 -0.1200 5.77 1.179 -0.1200 6.78 1.235 -0.1200 7.61 1.275 -0.1200 8.74 1.327 -0.1200 9.76 1.372 -0.1200 10.75 1.400 -0.1200 11.69 1.414 -0.1200 12.71 1.399 -0.1200 13.72 1.362 -0.1200 14.54 1.117 -0.1200 15.81 1.146 -0.1200 16.82 1.129 -0.1200 17.70 1.138 -0.1200 18.63 1.145 -0.1200 17.06 1.181 -0.1200 16.23 1.137 -0.1200 15.06 1.124 -0.1200 14.24 1.135 -0.1200 13.38 1.376 -0.1200 12.42 1.408 -0.1200 11.33 1.413 -0.1200 10.28 1.389 -0.1200 9.27 1.350 -0.1200 8.34 1.304 -0.1200 7.16 1.249 -0.1200 6.25 1.203 -0.1200 5.14 1.133 -0.1200 4.25 1.066 -0.1200 3.20 0.978 -0.1200 2.10 0.890 -0.1200 0.93 0.772 -0.1200 0.11 0.648 -0.1200 -1.05 0.573 -0.1200 -2.04 0.476 -0.1200 -2.93 0.387 -0.1200 -4.07 0.275 -0.1200 -5.30 0.160 -0.1200 -6.06 0.091 -0.1200 Tabulated from data in file AG00818.DAT & reduced using program Q02.00L Average Reynolds #: 300100 Number of angles of attack: 49 alpha / Cl / Cm -5.98 0.088 -0.1200 -4.62 0.210 -0.1200 -3.65 0.323 -0.1200 -2.58 0.438 -0.1200 -1.53 0.538 -0.1200 -0.39 0.659 -0.1200 0.56 0.754 -0.1200 1.67 0.851 -0.1200 2.67 0.933 -0.1200 3.66 1.016 -0.1200 4.67 1.095 -0.1200 5.80 1.168 -0.1200 6.77 1.221 -0.1200 7.88 1.281 -0.1200 8.72 1.327 -0.1200 10.00 1.390 -0.1200 10.84 1.417 -0.1200 11.99 1.419 -0.1200 12.83 1.395 -0.1200 13.90 1.352 -0.1200 14.37 1.207 -0.1200 15.49 1.196 -0.1200 16.44 1.184 -0.1200 17.45 1.174 -0.1200 18.44 1.141 -0.1200 17.36 1.148 -0.1200 16.34 1.187 -0.1200 15.30 1.200 -0.1200 14.33 1.262 -0.1200 13.56 1.360 -0.1200 12.20 1.413 -0.1200 11.36 1.424 -0.1200 10.15 1.393 -0.1200 9.16 1.349 -0.1200 8.05 1.288 -0.1200 7.01 1.231 -0.1200 6.24 1.190 -0.1200 5.00 1.114 -0.1200 4.07 1.046 -0.1200 3.21 0.976 -0.1200 2.03 0.876 -0.1200 1.24 0.815 -0.1200 -0.02 0.693 -0.1200 -0.96 0.591 -0.1200 -1.86 0.503 -0.1200 -2.97 0.392 -0.1200 -3.87 0.292 -0.1200 -5.05 0.162 -0.1200 -6.05 0.076 -0.1200 Tabulated from data in file CL00821.DAT & reduced using program Q02.00L File 7037bf10.lft created on 09-12-1997 at 13:46:19 using program FORMAT :::::::::::::: 7037BF5.LFT :::::::::::::: Airfoil: SD7037 (B) Builder: D. Thompson Comment: clean: flap = 5 degs Number of Reynolds #'s: 4 Average Reynolds #: 60600 Number of angles of attack: 49 alpha / Cl / Cm -5.96 -0.188 -0.1000 -4.54 -0.043 -0.1000 -3.44 0.056 -0.1000 -2.61 0.123 -0.1000 -1.50 0.219 -0.1000 -0.39 0.327 -0.1000 0.69 0.445 -0.1000 1.52 0.563 -0.1000 2.65 0.750 -0.1000 3.58 0.882 -0.1000 4.78 0.981 -0.1000 5.72 1.050 -0.1000 6.70 1.114 -0.1000 7.93 1.167 -0.1000 8.88 1.217 -0.1000 9.81 1.261 -0.1000 10.71 1.294 -0.1000 11.83 1.315 -0.1000 12.82 1.033 -0.1000 13.68 1.041 -0.1000 14.83 1.073 -0.1000 15.73 1.032 -0.1000 16.67 1.044 -0.1000 17.71 1.078 -0.1000 18.87 1.066 -0.1000 17.21 1.060 -0.1000 16.28 1.077 -0.1000 15.34 1.073 -0.1000 14.23 1.062 -0.1000 13.24 1.002 -0.1000 12.36 1.051 -0.1000 11.30 1.089 -0.1000 10.30 1.280 -0.1000 9.40 1.243 -0.1000 8.26 1.189 -0.1000 7.31 1.147 -0.1000 6.34 1.094 -0.1000 5.20 1.013 -0.1000 4.23 0.941 -0.1000 3.28 0.850 -0.1000 2.16 0.669 -0.1000 1.06 0.509 -0.1000 0.14 0.390 -0.1000 -0.89 0.294 -0.1000 -1.96 0.188 -0.1000 -2.89 0.116 -0.1000 -3.92 0.025 -0.1000 -4.98 -0.074 -0.1000 -6.00 -0.187 -0.1000 Tabulated from data in file CL00805.DAT & reduced using program Q02.00L Average Reynolds #: 100000 Number of angles of attack: 49 alpha / Cl / Cm -5.97 -0.099 -0.1000 -4.37 0.023 -0.1000 -3.47 0.118 -0.1000 -2.31 0.224 -0.1000 -1.42 0.278 -0.1000 -0.27 0.407 -0.1000 0.52 0.522 -0.1000 1.61 0.696 -0.1000 2.72 0.831 -0.1000 3.66 0.908 -0.1000 4.87 1.004 -0.1000 5.80 1.080 -0.1000 6.91 1.169 -0.1000 7.86 1.218 -0.1000 8.81 1.258 -0.1000 9.73 1.296 -0.1000 10.73 1.327 -0.1000 11.83 1.341 -0.1000 12.79 1.333 -0.1000 13.78 1.081 -0.1000 14.83 1.065 -0.1000 15.79 1.110 -0.1000 16.74 1.085 -0.1000 17.72 1.050 -0.1000 18.87 1.061 -0.1000 17.16 1.104 -0.1000 16.26 1.112 -0.1000 15.27 1.099 -0.1000 14.26 1.077 -0.1000 13.29 1.089 -0.1000 12.34 1.334 -0.1000 11.38 1.329 -0.1000 10.26 1.310 -0.1000 9.29 1.270 -0.1000 8.36 1.228 -0.1000 7.38 1.183 -0.1000 6.16 1.091 -0.1000 5.37 1.029 -0.1000 4.22 0.937 -0.1000 3.25 0.861 -0.1000 2.27 0.763 -0.1000 1.10 0.612 -0.1000 0.12 0.445 -0.1000 -0.95 0.315 -0.1000 -2.02 0.233 -0.1000 -3.00 0.157 -0.1000 -3.91 0.069 -0.1000 -5.04 -0.032 -0.1000 -5.97 -0.097 -0.1000 Tabulated from data in file CL00807.DAT & reduced using program Q02.00L Average Reynolds #: 200200 Number of angles of attack: 49 alpha / Cl / Cm -5.95 -0.013 -0.1000 -4.25 0.149 -0.1000 -3.29 0.238 -0.1000 -2.22 0.336 -0.1000 -1.36 0.423 -0.1000 -0.44 0.512 -0.1000 0.49 0.601 -0.1000 1.60 0.729 -0.1000 2.70 0.829 -0.1000 3.75 0.924 -0.1000 4.69 1.007 -0.1000 5.69 1.090 -0.1000 6.71 1.164 -0.1000 7.73 1.224 -0.1000 8.61 1.270 -0.1000 9.75 1.323 -0.1000 10.90 1.360 -0.1000 11.85 1.370 -0.1000 12.91 1.354 -0.1000 13.70 1.326 -0.1000 14.58 1.115 -0.1000 15.96 1.113 -0.1000 16.67 1.108 -0.1000 17.71 1.115 -0.1000 18.89 1.058 -0.1000 17.11 1.129 -0.1000 16.23 1.123 -0.1000 14.98 1.081 -0.1000 14.12 1.092 -0.1000 13.28 1.336 -0.1000 12.30 1.367 -0.1000 11.34 1.365 -0.1000 10.35 1.339 -0.1000 9.30 1.296 -0.1000 8.35 1.249 -0.1000 7.23 1.187 -0.1000 6.09 1.112 -0.1000 5.16 1.036 -0.1000 4.26 0.958 -0.1000 3.16 0.858 -0.1000 2.03 0.760 -0.1000 1.21 0.663 -0.1000 -0.02 0.535 -0.1000 -0.90 0.464 -0.1000 -2.00 0.356 -0.1000 -3.02 0.258 -0.1000 -4.07 0.161 -0.1000 -5.03 0.069 -0.1000 -6.15 -0.034 -0.1000 Tabulated from data in file CL00809.DAT & reduced using program Q02.00L Average Reynolds #: 300100 Number of angles of attack: 49 alpha / Cl / Cm -5.91 -0.014 -0.1000 -4.45 0.125 -0.1000 -3.50 0.215 -0.1000 -2.66 0.324 -0.1000 -1.41 0.455 -0.1000 -0.53 0.539 -0.1000 0.49 0.633 -0.1000 1.62 0.742 -0.1000 2.77 0.848 -0.1000 3.72 0.935 -0.1000 4.62 1.015 -0.1000 5.81 1.115 -0.1000 6.73 1.181 -0.1000 7.79 1.248 -0.1000 8.90 1.312 -0.1000 9.72 1.354 -0.1000 10.80 1.396 -0.1000 11.80 1.407 -0.1000 12.83 1.384 -0.1000 13.68 1.352 -0.1000 14.94 1.307 -0.1000 15.47 1.158 -0.1000 16.60 1.173 -0.1000 17.58 1.142 -0.1000 18.52 1.122 -0.1000 17.35 1.131 -0.1000 16.36 1.184 -0.1000 15.30 1.168 -0.1000 14.73 1.314 -0.1000 13.27 1.367 -0.1000 12.36 1.394 -0.1000 11.26 1.401 -0.1000 10.34 1.378 -0.1000 9.25 1.326 -0.1000 8.17 1.264 -0.1000 7.25 1.207 -0.1000 6.08 1.129 -0.1000 5.13 1.052 -0.1000 4.25 0.975 -0.1000 3.15 0.874 -0.1000 2.10 0.774 -0.1000 1.06 0.677 -0.1000 0.07 0.582 -0.1000 -0.87 0.490 -0.1000 -1.96 0.379 -0.1000 -3.11 0.238 -0.1000 -3.88 0.159 -0.1000 -5.11 0.047 -0.1000 -6.05 -0.041 -0.1000 Tabulated from data in file CL00811.DAT & reduced using program Q02.00L File 7037bf5.lft created on 09-12-1997 at 13:46:18 using program FORMAT :::::::::::::: 7037C.LFT :::::::::::::: Airfoil: SD7037 (C) Builder: D. Brengman Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60300 Number of angles of attack: 49 alpha / Cl / Cm -6.39 -0.370 -0.0850 -5.27 -0.285 -0.0850 -4.20 -0.208 -0.0850 -3.12 -0.121 -0.0850 -2.21 -0.048 -0.0850 -1.20 0.052 -0.0850 -0.07 0.173 -0.0850 0.93 0.318 -0.0850 1.94 0.449 -0.0850 2.98 0.591 -0.0850 4.03 0.704 -0.0850 5.10 0.804 -0.0850 6.02 0.881 -0.0850 7.14 0.975 -0.0850 8.07 1.042 -0.0850 9.13 1.097 -0.0850 10.20 1.165 -0.0850 11.12 1.210 -0.0850 12.13 1.240 -0.0850 13.09 1.243 -0.0850 14.16 0.999 -0.0850 15.06 1.034 -0.0850 16.07 1.001 -0.0850 17.12 1.041 -0.0850 18.11 0.987 -0.0850 16.88 1.014 -0.0850 15.91 1.033 -0.0850 14.87 1.018 -0.0850 13.88 0.991 -0.0850 12.89 1.027 -0.0850 11.96 1.214 -0.0850 11.00 1.184 -0.0850 9.93 1.123 -0.0850 8.90 1.059 -0.0850 7.90 1.003 -0.0850 6.88 0.925 -0.0850 5.91 0.841 -0.0850 4.77 0.743 -0.0850 3.73 0.640 -0.0850 2.83 0.533 -0.0850 1.74 0.392 -0.0850 0.70 0.250 -0.0850 -0.35 0.104 -0.0850 -1.34 0.009 -0.0850 -2.42 -0.087 -0.0850 -3.38 -0.162 -0.0850 -4.42 -0.239 -0.0850 -5.49 -0.316 -0.0850 -6.43 -0.389 -0.0850 Tabulated from data in file CL00623.DAT & reduced using program Q02.00L Average Reynolds #: 100700 Number of angles of attack: 49 alpha / Cl / Cm -6.47 -0.403 -0.0850 -5.25 -0.287 -0.0850 -4.27 -0.212 -0.0850 -3.25 -0.123 -0.0850 -2.23 -0.023 -0.0850 -1.17 0.093 -0.0850 -0.10 0.270 -0.0850 0.96 0.418 -0.0850 2.01 0.533 -0.0850 3.08 0.637 -0.0850 4.01 0.721 -0.0850 5.18 0.829 -0.0850 6.14 0.910 -0.0850 7.14 0.992 -0.0850 8.11 1.073 -0.0850 9.09 1.127 -0.0850 10.19 1.194 -0.0850 11.27 1.243 -0.0850 12.14 1.251 -0.0850 13.17 1.246 -0.0850 14.09 1.051 -0.0850 15.16 1.059 -0.0850 16.09 0.999 -0.0850 17.04 0.981 -0.0850 18.18 1.009 -0.0850 16.89 0.985 -0.0850 15.92 1.022 -0.0850 14.84 1.060 -0.0850 13.92 1.026 -0.0850 12.95 1.237 -0.0850 12.02 1.239 -0.0850 10.98 1.215 -0.0850 9.94 1.160 -0.0850 8.94 1.101 -0.0850 7.92 1.041 -0.0850 6.84 0.951 -0.0850 5.87 0.867 -0.0850 4.87 0.778 -0.0850 3.75 0.675 -0.0850 2.79 0.589 -0.0850 1.76 0.485 -0.0850 0.76 0.373 -0.0850 -0.25 0.232 -0.0850 -1.39 0.055 -0.0850 -2.38 -0.049 -0.0850 -3.40 -0.146 -0.0850 -4.36 -0.226 -0.0850 -5.44 -0.307 -0.0850 -6.54 -0.410 -0.0850 Tabulated from data in file CL00625.DAT & reduced using program Q02.00L Average Reynolds #: 201000 Number of angles of attack: 49 alpha / Cl / Cm -6.48 -0.417 -0.0850 -5.18 -0.260 -0.0850 -4.26 -0.160 -0.0850 -3.11 -0.019 -0.0850 -2.17 0.110 -0.0850 -0.97 0.230 -0.0850 -0.00 0.326 -0.0850 0.96 0.418 -0.0850 2.10 0.534 -0.0850 3.02 0.628 -0.0850 3.99 0.725 -0.0850 5.09 0.831 -0.0850 6.05 0.921 -0.0850 7.15 1.016 -0.0850 8.15 1.092 -0.0850 9.08 1.156 -0.0850 10.16 1.223 -0.0850 11.18 1.268 -0.0850 12.12 1.277 -0.0850 13.12 1.259 -0.0850 14.11 1.242 -0.0850 15.15 1.210 -0.0850 15.91 1.121 -0.0850 17.25 1.082 -0.0850 18.24 1.017 -0.0850 16.91 1.108 -0.0850 15.87 1.125 -0.0850 14.84 1.134 -0.0850 14.00 1.248 -0.0850 12.99 1.262 -0.0850 12.03 1.278 -0.0850 11.03 1.260 -0.0850 9.99 1.209 -0.0850 8.94 1.139 -0.0850 7.93 1.069 -0.0850 6.85 0.982 -0.0850 5.89 0.899 -0.0850 4.81 0.800 -0.0850 3.80 0.699 -0.0850 2.74 0.593 -0.0850 1.68 0.484 -0.0850 0.70 0.387 -0.0850 -0.30 0.290 -0.0850 -1.32 0.193 -0.0850 -2.48 0.060 -0.0850 -3.37 -0.061 -0.0850 -4.55 -0.197 -0.0850 -5.51 -0.303 -0.0850 -6.50 -0.416 -0.0850 Tabulated from data in file CL00627.DAT & reduced using program Q02.00L Average Reynolds #: 301100 Number of angles of attack: 49 alpha / Cl / Cm -6.49 -0.393 -0.0850 -5.24 -0.217 -0.0850 -4.16 -0.091 -0.0850 -3.14 0.015 -0.0850 -2.00 0.120 -0.0850 -0.98 0.211 -0.0850 0.01 0.307 -0.0850 1.10 0.425 -0.0850 1.99 0.517 -0.0850 3.01 0.623 -0.0850 4.08 0.731 -0.0850 5.16 0.834 -0.0850 6.04 0.914 -0.0850 7.12 1.006 -0.0850 8.17 1.090 -0.0850 9.14 1.163 -0.0850 10.24 1.235 -0.0850 11.27 1.277 -0.0850 12.23 1.279 -0.0850 13.16 1.261 -0.0850 14.25 1.232 -0.0850 15.20 1.194 -0.0850 15.92 1.224 -0.0850 17.12 1.153 -0.0850 18.14 1.158 -0.0850 16.82 1.165 -0.0850 15.79 1.206 -0.0850 15.22 1.190 -0.0850 13.90 1.243 -0.0850 12.93 1.264 -0.0850 11.98 1.280 -0.0850 10.93 1.262 -0.0850 9.91 1.211 -0.0850 8.86 1.138 -0.0850 7.81 1.057 -0.0850 6.83 0.976 -0.0850 5.70 0.877 -0.0850 4.79 0.791 -0.0850 3.68 0.682 -0.0850 2.72 0.584 -0.0850 1.71 0.480 -0.0850 0.61 0.366 -0.0850 -0.51 0.247 -0.0850 -1.47 0.162 -0.0850 -2.45 0.076 -0.0850 -3.61 -0.037 -0.0850 -4.52 -0.139 -0.0850 -5.51 -0.255 -0.0850 -6.52 -0.400 -0.0850 Tabulated from data in file CL00629.DAT & reduced using program Q02.00L File 7037c.lft created on 09-12-1997 at 13:46:19 using program FORMAT :::::::::::::: 7037CBF4.LFT :::::::::::::: Airfoil: SD7037 (C) Builder: D. Brengman Comment: gurney flap (h/c = 0.4%) Number of Reynolds #'s: 4 Average Reynolds #: 60300 Number of angles of attack: 51 alpha / Cl / Cm -5.57 -0.249 -0.0850 -3.90 -0.137 -0.0850 -2.97 -0.062 -0.0850 -2.08 0.004 -0.0850 -0.93 0.117 -0.0850 -0.06 0.205 -0.0850 1.14 0.376 -0.0850 2.02 0.492 -0.0850 3.20 0.634 -0.0850 4.08 0.721 -0.0850 5.30 0.829 -0.0850 6.21 0.903 -0.0850 7.15 0.978 -0.0850 8.38 1.065 -0.0850 9.27 1.128 -0.0850 10.20 1.184 -0.0850 11.38 1.224 -0.0850 12.22 1.234 -0.0850 13.25 1.068 -0.0850 14.37 1.075 -0.0850 15.36 1.034 -0.0850 16.26 1.037 -0.0850 17.22 1.026 -0.0850 18.33 1.051 -0.0850 19.23 1.032 -0.0850 20.42 1.061 -0.0850 18.75 1.107 -0.0850 17.85 1.097 -0.0850 16.76 1.093 -0.0850 15.66 1.106 -0.0850 14.67 1.098 -0.0850 13.82 1.050 -0.0850 12.85 1.081 -0.0850 11.70 1.073 -0.0850 10.81 1.239 -0.0850 9.89 1.206 -0.0850 8.70 1.130 -0.0850 7.83 1.068 -0.0850 6.81 0.986 -0.0850 5.60 0.899 -0.0850 4.79 0.836 -0.0850 3.55 0.722 -0.0850 2.72 0.634 -0.0850 1.68 0.511 -0.0850 0.49 0.345 -0.0850 -0.33 0.242 -0.0850 -1.50 0.131 -0.0850 -2.50 0.054 -0.0850 -3.47 -0.020 -0.0850 -4.65 -0.118 -0.0850 -5.64 -0.184 -0.0850 Tabulated from data in file CN00900.DAT & reduced using program Q02.00L Average Reynolds #: 100300 Number of angles of attack: 51 alpha / Cl / Cm -5.57 -0.248 -0.0850 -4.08 -0.105 -0.0850 -2.87 0.023 -0.0850 -1.96 0.108 -0.0850 -1.02 0.187 -0.0850 0.21 0.380 -0.0850 1.02 0.485 -0.0850 2.26 0.614 -0.0850 3.16 0.703 -0.0850 4.33 0.818 -0.0850 5.24 0.907 -0.0850 6.16 0.991 -0.0850 7.28 1.091 -0.0850 8.43 1.166 -0.0850 9.34 1.227 -0.0850 10.28 1.285 -0.0850 11.56 1.320 -0.0850 12.33 1.326 -0.0850 13.18 1.313 -0.0850 14.67 1.157 -0.0850 15.39 1.123 -0.0850 16.32 1.075 -0.0850 17.43 1.087 -0.0850 18.38 1.054 -0.0850 19.60 1.072 -0.0850 20.24 1.075 -0.0850 18.98 1.047 -0.0850 18.04 1.081 -0.0850 17.12 1.103 -0.0850 15.71 1.107 -0.0850 14.67 1.162 -0.0850 13.75 1.148 -0.0850 12.98 1.103 -0.0850 11.94 1.320 -0.0850 10.75 1.310 -0.0850 9.74 1.264 -0.0850 8.83 1.195 -0.0850 7.69 1.128 -0.0850 6.79 1.055 -0.0850 5.73 0.962 -0.0850 4.73 0.867 -0.0850 3.70 0.769 -0.0850 2.74 0.674 -0.0850 1.50 0.554 -0.0850 0.66 0.459 -0.0850 -0.59 0.278 -0.0850 -1.40 0.156 -0.0850 -3.04 0.074 -0.0850 -3.44 0.016 -0.0850 -4.80 -0.115 -0.0850 -6.05 -0.219 -0.0850 Tabulated from data in file CN00902.DAT & reduced using program Q02.00L Average Reynolds #: 200400 Number of angles of attack: 51 alpha / Cl / Cm -5.56 -0.198 -0.0850 -3.80 -0.014 -0.0850 -3.03 0.079 -0.0850 -1.91 0.240 -0.0850 -0.95 0.328 -0.0850 0.32 0.416 -0.0850 1.05 0.492 -0.0850 2.11 0.606 -0.0850 3.18 0.722 -0.0850 4.25 0.833 -0.0850 5.30 0.937 -0.0850 6.35 1.036 -0.0850 7.40 1.127 -0.0850 8.40 1.203 -0.0850 9.42 1.274 -0.0850 10.39 1.326 -0.0850 11.34 1.349 -0.0850 12.27 1.334 -0.0850 13.46 1.309 -0.0850 14.23 1.285 -0.0850 15.20 1.220 -0.0850 16.33 1.170 -0.0850 17.36 1.079 -0.0850 18.26 1.075 -0.0850 19.38 1.070 -0.0850 20.40 1.074 -0.0850 18.66 1.076 -0.0850 17.69 1.083 -0.0850 16.61 1.142 -0.0850 15.56 1.195 -0.0850 14.65 1.214 -0.0850 13.78 1.210 -0.0850 12.74 1.325 -0.0850 11.83 1.346 -0.0850 10.80 1.341 -0.0850 9.74 1.291 -0.0850 8.88 1.235 -0.0850 7.66 1.143 -0.0850 6.73 1.064 -0.0850 5.66 0.965 -0.0850 4.74 0.873 -0.0850 3.69 0.766 -0.0850 2.51 0.641 -0.0850 1.56 0.541 -0.0850 0.37 0.416 -0.0850 -0.62 0.325 -0.0850 -1.60 0.275 -0.0850 -2.63 0.129 -0.0850 -3.65 -0.006 -0.0850 -4.56 -0.104 -0.0850 -5.72 -0.221 -0.0850 Tabulated from data in file CN00904.DAT & reduced using program Q02.00L Average Reynolds #: 300500 Number of angles of attack: 51 alpha / Cl / Cm -5.67 -0.194 -0.0850 -3.83 0.023 -0.0850 -2.97 0.132 -0.0850 -1.80 0.266 -0.0850 -0.92 0.348 -0.0850 0.24 0.408 -0.0850 1.30 0.528 -0.0850 2.36 0.647 -0.0850 3.12 0.729 -0.0850 4.48 0.874 -0.0850 5.28 0.952 -0.0850 6.32 1.052 -0.0850 7.35 1.142 -0.0850 8.39 1.229 -0.0850 9.36 1.303 -0.0850 10.34 1.359 -0.0850 11.29 1.378 -0.0850 12.46 1.361 -0.0850 13.26 1.336 -0.0850 14.45 1.285 -0.0850 15.29 1.258 -0.0850 15.99 1.269 -0.0850 17.11 1.168 -0.0850 18.18 1.095 -0.0850 19.10 1.077 -0.0850 20.09 1.072 -0.0850 18.65 1.081 -0.0850 17.69 1.102 -0.0850 16.69 1.221 -0.0850 15.80 1.260 -0.0850 14.93 1.304 -0.0850 13.65 1.317 -0.0850 12.76 1.352 -0.0850 11.67 1.372 -0.0850 10.86 1.370 -0.0850 9.76 1.323 -0.0850 8.73 1.252 -0.0850 7.53 1.156 -0.0850 6.48 1.063 -0.0850 5.54 0.977 -0.0850 4.52 0.875 -0.0850 3.47 0.764 -0.0850 2.54 0.663 -0.0850 1.44 0.541 -0.0850 0.65 0.454 -0.0850 -0.46 0.364 -0.0850 -1.51 0.295 -0.0850 -2.53 0.187 -0.0850 -3.47 0.070 -0.0850 -4.54 -0.064 -0.0850 -5.81 -0.205 -0.0850 Tabulated from data in file AG00906.DAT & reduced using program Q02.00L File 7037cbf4.lft created on 09-12-1997 at 13:46:19 using program FORMAT :::::::::::::: 7075AT1.LFT :::::::::::::: Airfoil: S7075 (A) Builder: J. Robertson Comment: plain trip @ x/c = 68% (h/c = 0.17%; w/c = 2.0%) Number of Reynolds #'s: 3 Average Reynolds #: 100800 Number of angles of attack: 49 alpha / Cl / Cm -6.13 -0.411 -0.0800 -4.81 -0.242 -0.0800 -3.82 -0.155 -0.0800 -2.79 -0.052 -0.0800 -1.85 0.040 -0.0800 -0.67 0.138 -0.0800 0.23 0.246 -0.0800 1.31 0.382 -0.0800 2.41 0.553 -0.0800 3.35 0.674 -0.0800 4.46 0.783 -0.0800 5.54 0.873 -0.0800 6.52 0.949 -0.0800 7.44 1.023 -0.0800 8.49 1.092 -0.0800 9.51 1.130 -0.0800 10.63 1.176 -0.0800 11.53 1.203 -0.0800 12.61 1.214 -0.0800 13.56 1.085 -0.0800 14.53 1.021 -0.0800 15.51 1.014 -0.0800 16.58 1.018 -0.0800 17.46 1.014 -0.0800 18.54 0.952 -0.0800 17.17 1.005 -0.0800 16.02 1.000 -0.0800 15.18 1.018 -0.0800 14.16 1.067 -0.0800 13.21 1.177 -0.0800 12.31 1.218 -0.0800 11.16 1.192 -0.0800 10.11 1.152 -0.0800 9.19 1.115 -0.0800 8.04 1.065 -0.0800 7.18 0.999 -0.0800 6.19 0.920 -0.0800 4.99 0.820 -0.0800 3.95 0.728 -0.0800 3.11 0.640 -0.0800 2.02 0.491 -0.0800 0.97 0.330 -0.0800 0.01 0.206 -0.0800 -1.11 0.084 -0.0800 -2.03 0.020 -0.0800 -3.15 -0.096 -0.0800 -4.11 -0.178 -0.0800 -5.13 -0.277 -0.0800 -6.14 -0.403 -0.0800 Tabulated from data in file CL00699.DAT & reduced using program Q02.00L Average Reynolds #: 200800 Number of angles of attack: 49 alpha / Cl / Cm -6.15 -0.283 -0.0800 -4.73 -0.116 -0.0800 -3.62 -0.014 -0.0800 -2.70 0.077 -0.0800 -1.58 0.186 -0.0800 -0.67 0.271 -0.0800 0.35 0.355 -0.0800 1.36 0.469 -0.0800 2.35 0.570 -0.0800 3.45 0.689 -0.0800 4.45 0.790 -0.0800 5.55 0.884 -0.0800 6.46 0.956 -0.0800 7.54 1.037 -0.0800 8.61 1.102 -0.0800 9.65 1.151 -0.0800 10.64 1.189 -0.0800 11.54 1.216 -0.0800 12.65 1.225 -0.0800 13.46 1.138 -0.0800 14.51 1.047 -0.0800 15.53 1.010 -0.0800 16.45 1.002 -0.0800 17.58 0.966 -0.0800 18.49 0.951 -0.0800 17.04 0.996 -0.0800 16.14 1.012 -0.0800 15.13 1.040 -0.0800 14.11 1.123 -0.0800 13.34 1.211 -0.0800 12.13 1.222 -0.0800 11.11 1.201 -0.0800 10.15 1.166 -0.0800 9.09 1.117 -0.0800 8.12 1.070 -0.0800 7.09 0.998 -0.0800 5.98 0.909 -0.0800 5.09 0.834 -0.0800 4.13 0.752 -0.0800 2.94 0.617 -0.0800 2.02 0.527 -0.0800 0.81 0.400 -0.0800 -0.12 0.300 -0.0800 -1.25 0.214 -0.0800 -2.23 0.121 -0.0800 -3.21 0.022 -0.0800 -4.19 -0.072 -0.0800 -5.27 -0.173 -0.0800 -6.30 -0.304 -0.0800 Tabulated from data in file CL00701.DAT & reduced using program Q02.00L Average Reynolds #: 300900 Number of angles of attack: 49 alpha / Cl / Cm -6.13 -0.265 -0.0800 -4.79 -0.122 -0.0800 -3.75 -0.028 -0.0800 -2.63 0.078 -0.0800 -1.56 0.166 -0.0800 -0.66 0.257 -0.0800 0.45 0.396 -0.0800 1.43 0.498 -0.0800 2.43 0.605 -0.0800 3.48 0.709 -0.0800 4.50 0.803 -0.0800 5.49 0.890 -0.0800 6.46 0.972 -0.0800 7.62 1.062 -0.0800 8.55 1.123 -0.0800 9.61 1.183 -0.0800 10.60 1.223 -0.0800 11.55 1.249 -0.0800 12.54 1.258 -0.0800 13.56 1.249 -0.0800 14.43 1.130 -0.0800 15.40 1.070 -0.0800 16.36 1.050 -0.0800 17.34 1.009 -0.0800 18.42 0.966 -0.0800 17.05 1.010 -0.0800 15.97 1.045 -0.0800 14.97 1.092 -0.0800 14.26 1.171 -0.0800 13.24 1.249 -0.0800 12.25 1.257 -0.0800 11.21 1.238 -0.0800 10.07 1.198 -0.0800 9.15 1.151 -0.0800 8.18 1.094 -0.0800 7.02 1.007 -0.0800 5.99 0.924 -0.0800 5.11 0.848 -0.0800 3.92 0.739 -0.0800 3.02 0.656 -0.0800 1.99 0.548 -0.0800 0.88 0.433 -0.0800 -0.13 0.323 -0.0800 -1.16 0.203 -0.0800 -2.32 0.103 -0.0800 -3.33 0.004 -0.0800 -4.32 -0.086 -0.0800 -5.36 -0.183 -0.0800 -6.23 -0.278 -0.0800 Tabulated from data in file CL00704.DAT & reduced using program Q02.00L File 7075at1.lft created on 09-12-1997 at 13:46:18 using program FORMAT :::::::::::::: 7075AT2.LFT :::::::::::::: Airfoil: S7075 (A) Builder: J. Robertson Comment: Zig-Zag trip type "D" @ x/c = 68% (h/c = 0.25%) Number of Reynolds #'s: 4 Average Reynolds #: 60500 Number of angles of attack: 49 alpha / Cl / Cm -6.13 -0.370 -0.0800 -4.78 -0.259 -0.0800 -3.81 -0.174 -0.0800 -2.83 -0.091 -0.0800 -1.89 -0.014 -0.0800 -0.75 0.100 -0.0800 0.29 0.206 -0.0800 1.38 0.320 -0.0800 2.35 0.451 -0.0800 3.45 0.628 -0.0800 4.42 0.761 -0.0800 5.56 0.856 -0.0800 6.57 0.937 -0.0800 7.55 1.008 -0.0800 8.49 1.061 -0.0800 9.61 1.112 -0.0800 10.50 1.152 -0.0800 11.57 1.189 -0.0800 12.62 1.203 -0.0800 13.60 1.044 -0.0800 14.43 0.974 -0.0800 15.52 1.004 -0.0800 16.55 0.978 -0.0800 17.45 0.986 -0.0800 18.56 1.025 -0.0800 17.17 1.008 -0.0800 16.15 1.016 -0.0800 15.25 1.005 -0.0800 14.13 0.985 -0.0800 13.17 1.057 -0.0800 12.21 1.196 -0.0800 11.27 1.180 -0.0800 10.09 1.133 -0.0800 9.13 1.090 -0.0800 8.16 1.038 -0.0800 7.15 0.971 -0.0800 6.13 0.897 -0.0800 5.19 0.821 -0.0800 4.10 0.689 -0.0800 3.04 0.538 -0.0800 1.99 0.379 -0.0800 0.97 0.254 -0.0800 -0.04 0.158 -0.0800 -1.11 0.054 -0.0800 -2.15 -0.042 -0.0800 -3.08 -0.121 -0.0800 -4.05 -0.200 -0.0800 -5.17 -0.293 -0.0800 -6.09 -0.377 -0.0800 Tabulated from data in file CL00706.DAT & reduced using program Q02.00L Average Reynolds #: 100500 Number of angles of attack: 49 alpha / Cl / Cm -6.10 -0.291 -0.0800 -4.84 -0.154 -0.0800 -3.73 -0.051 -0.0800 -2.79 0.037 -0.0800 -1.66 0.118 -0.0800 -0.72 0.195 -0.0800 0.23 0.250 -0.0800 1.41 0.394 -0.0800 2.45 0.556 -0.0800 3.49 0.687 -0.0800 4.52 0.785 -0.0800 5.56 0.874 -0.0800 6.60 0.960 -0.0800 7.64 1.039 -0.0800 8.45 1.089 -0.0800 9.66 1.136 -0.0800 10.66 1.174 -0.0800 11.61 1.205 -0.0800 12.54 1.215 -0.0800 13.62 1.086 -0.0800 14.43 0.997 -0.0800 15.56 0.994 -0.0800 16.53 0.998 -0.0800 17.53 1.004 -0.0800 18.62 0.981 -0.0800 17.09 0.998 -0.0800 16.10 0.994 -0.0800 15.15 1.011 -0.0800 13.99 1.034 -0.0800 13.12 1.163 -0.0800 12.14 1.210 -0.0800 11.23 1.188 -0.0800 10.19 1.149 -0.0800 9.11 1.104 -0.0800 8.21 1.069 -0.0800 7.01 0.977 -0.0800 6.06 0.904 -0.0800 5.05 0.823 -0.0800 4.05 0.732 -0.0800 3.08 0.630 -0.0800 2.05 0.481 -0.0800 1.02 0.340 -0.0800 -0.16 0.209 -0.0800 -1.09 0.161 -0.0800 -2.02 0.100 -0.0800 -3.21 0.000 -0.0800 -4.17 -0.090 -0.0800 -5.15 -0.174 -0.0800 -6.13 -0.275 -0.0800 Tabulated from data in file CL00708.DAT & reduced using program Q02.00L Average Reynolds #: 200600 Number of angles of attack: 49 alpha / Cl / Cm -6.20 -0.306 -0.0800 -4.69 -0.137 -0.0800 -3.77 -0.055 -0.0800 -2.60 0.055 -0.0800 -1.65 0.145 -0.0800 -0.65 0.234 -0.0800 0.39 0.340 -0.0800 1.29 0.442 -0.0800 2.45 0.574 -0.0800 3.35 0.661 -0.0800 4.46 0.787 -0.0800 5.65 0.885 -0.0800 6.64 0.962 -0.0800 7.60 1.036 -0.0800 8.66 1.097 -0.0800 9.55 1.140 -0.0800 10.60 1.180 -0.0800 11.62 1.209 -0.0800 12.61 1.216 -0.0800 13.40 1.152 -0.0800 14.52 1.047 -0.0800 15.60 0.998 -0.0800 16.50 0.997 -0.0800 17.70 0.969 -0.0800 18.73 0.974 -0.0800 16.88 0.988 -0.0800 16.00 0.993 -0.0800 15.05 1.012 -0.0800 14.04 1.119 -0.0800 13.25 1.208 -0.0800 12.09 1.214 -0.0800 11.19 1.196 -0.0800 10.07 1.155 -0.0800 9.03 1.108 -0.0800 8.18 1.066 -0.0800 7.00 0.983 -0.0800 6.04 0.908 -0.0800 5.05 0.825 -0.0800 4.03 0.733 -0.0800 2.97 0.611 -0.0800 1.98 0.509 -0.0800 0.95 0.392 -0.0800 -0.08 0.278 -0.0800 -1.01 0.192 -0.0800 -2.06 0.100 -0.0800 -3.11 -0.002 -0.0800 -4.24 -0.104 -0.0800 -5.17 -0.185 -0.0800 -6.27 -0.308 -0.0800 Tabulated from data in file CL00710.DAT & reduced using program Q02.00L Average Reynolds #: 301100 Number of angles of attack: 49 alpha / Cl / Cm -6.13 -0.283 -0.0800 -4.80 -0.141 -0.0800 -3.66 -0.037 -0.0800 -2.68 0.054 -0.0800 -1.56 0.152 -0.0800 -0.53 0.247 -0.0800 0.32 0.364 -0.0800 1.32 0.474 -0.0800 2.62 0.617 -0.0800 3.44 0.698 -0.0800 4.51 0.795 -0.0800 5.59 0.890 -0.0800 6.66 0.976 -0.0800 7.70 1.058 -0.0800 8.68 1.119 -0.0800 9.61 1.171 -0.0800 10.65 1.213 -0.0800 11.65 1.240 -0.0800 12.61 1.250 -0.0800 13.47 1.229 -0.0800 14.50 1.149 -0.0800 15.49 1.060 -0.0800 16.35 1.043 -0.0800 17.45 1.014 -0.0800 18.38 0.986 -0.0800 17.06 1.023 -0.0800 16.08 1.048 -0.0800 14.98 1.108 -0.0800 14.14 1.163 -0.0800 13.53 1.240 -0.0800 12.19 1.246 -0.0800 11.23 1.227 -0.0800 10.02 1.185 -0.0800 9.01 1.133 -0.0800 8.09 1.081 -0.0800 7.07 1.005 -0.0800 5.93 0.913 -0.0800 5.00 0.834 -0.0800 3.98 0.740 -0.0800 2.94 0.641 -0.0800 1.89 0.531 -0.0800 0.81 0.411 -0.0800 -0.17 0.273 -0.0800 -1.29 0.172 -0.0800 -2.45 0.070 -0.0800 -3.21 -0.002 -0.0800 -4.29 -0.098 -0.0800 -5.35 -0.194 -0.0800 -6.27 -0.298 -0.0800 Tabulated from data in file CL00712.DAT & reduced using program Q02.00L File 7075at2.lft created on 09-12-1997 at 13:46:18 using program FORMAT :::::::::::::: 7075AT3.LFT :::::::::::::: Airfoil: S7075 (A) Builder: J. Robertson Comment: Zig-Zag trip type "D" @ x/c = 68% (h/c = 0.39%) Number of Reynolds #'s: 3 Average Reynolds #: 100400 Number of angles of attack: 49 alpha / Cl / Cm -6.15 -0.285 -0.0800 -4.56 -0.119 -0.0800 -3.62 -0.035 -0.0800 -2.73 0.048 -0.0800 -1.64 0.136 -0.0800 -0.77 0.235 -0.0800 0.27 0.306 -0.0800 1.56 0.432 -0.0800 2.45 0.568 -0.0800 3.55 0.702 -0.0800 4.52 0.794 -0.0800 5.50 0.877 -0.0800 6.68 0.962 -0.0800 7.44 1.027 -0.0800 8.61 1.097 -0.0800 9.73 1.143 -0.0800 10.66 1.182 -0.0800 11.54 1.204 -0.0800 12.52 1.214 -0.0800 13.51 1.041 -0.0800 14.50 1.026 -0.0800 15.70 1.003 -0.0800 16.64 1.019 -0.0800 17.47 0.989 -0.0800 18.59 0.964 -0.0800 17.15 1.003 -0.0800 16.01 1.028 -0.0800 15.11 1.011 -0.0800 14.01 1.053 -0.0800 13.07 1.144 -0.0800 12.07 1.218 -0.0800 11.06 1.191 -0.0800 10.03 1.149 -0.0800 9.09 1.110 -0.0800 8.10 1.072 -0.0800 7.03 0.982 -0.0800 5.94 0.897 -0.0800 5.03 0.831 -0.0800 4.08 0.743 -0.0800 2.95 0.622 -0.0800 2.06 0.498 -0.0800 0.95 0.356 -0.0800 -0.18 0.292 -0.0800 -1.20 0.176 -0.0800 -2.18 0.087 -0.0800 -3.08 0.011 -0.0800 -4.20 -0.089 -0.0800 -5.17 -0.175 -0.0800 -6.16 -0.279 -0.0800 Tabulated from data in file CL00716.DAT & reduced using program Q02.00L Average Reynolds #: 200700 Number of angles of attack: 49 alpha / Cl / Cm -6.12 -0.281 -0.0800 -4.65 -0.121 -0.0800 -3.61 -0.025 -0.0800 -2.53 0.075 -0.0800 -1.54 0.168 -0.0800 -0.50 0.266 -0.0800 0.40 0.358 -0.0800 1.40 0.467 -0.0800 2.40 0.579 -0.0800 3.67 0.713 -0.0800 4.47 0.790 -0.0800 5.73 0.896 -0.0800 6.49 0.957 -0.0800 7.51 1.038 -0.0800 8.52 1.102 -0.0800 9.76 1.160 -0.0800 10.70 1.194 -0.0800 11.61 1.221 -0.0800 12.53 1.232 -0.0800 13.39 1.178 -0.0800 14.60 1.071 -0.0800 15.54 1.040 -0.0800 16.59 1.019 -0.0800 17.58 0.983 -0.0800 18.70 0.965 -0.0800 16.94 1.026 -0.0800 16.02 1.007 -0.0800 15.13 1.052 -0.0800 13.98 1.144 -0.0800 13.22 1.228 -0.0800 12.20 1.229 -0.0800 11.18 1.205 -0.0800 9.96 1.162 -0.0800 9.13 1.123 -0.0800 7.93 1.057 -0.0800 6.94 0.982 -0.0800 5.89 0.896 -0.0800 5.11 0.831 -0.0800 4.01 0.732 -0.0800 2.96 0.625 -0.0800 1.93 0.512 -0.0800 0.80 0.391 -0.0800 -0.06 0.301 -0.0800 -1.31 0.180 -0.0800 -2.18 0.104 -0.0800 -3.13 0.015 -0.0800 -4.33 -0.094 -0.0800 -5.32 -0.182 -0.0800 -6.31 -0.297 -0.0800 Tabulated from data in file CL00718.DAT & reduced using program Q02.00L Average Reynolds #: 301100 Number of angles of attack: 49 alpha / Cl / Cm -5.88 -0.234 -0.0800 -4.36 -0.086 -0.0800 -3.32 0.009 -0.0800 -2.62 0.076 -0.0800 -1.38 0.184 -0.0800 -0.60 0.254 -0.0800 0.58 0.383 -0.0800 1.68 0.504 -0.0800 2.77 0.624 -0.0800 3.56 0.704 -0.0800 4.44 0.780 -0.0800 5.62 0.886 -0.0800 6.53 0.962 -0.0800 7.52 1.040 -0.0800 8.62 1.111 -0.0800 9.55 1.163 -0.0800 10.56 1.200 -0.0800 11.70 1.229 -0.0800 12.75 1.241 -0.0800 13.62 1.236 -0.0800 14.61 1.145 -0.0800 15.44 1.074 -0.0800 16.50 1.035 -0.0800 17.49 1.008 -0.0800 18.53 0.946 -0.0800 16.83 1.028 -0.0800 16.06 1.047 -0.0800 15.17 1.085 -0.0800 13.98 1.213 -0.0800 13.45 1.236 -0.0800 12.12 1.235 -0.0800 10.95 1.208 -0.0800 10.00 1.177 -0.0800 9.04 1.128 -0.0800 7.95 1.061 -0.0800 6.89 0.979 -0.0800 5.77 0.888 -0.0800 4.91 0.811 -0.0800 3.93 0.723 -0.0800 2.99 0.632 -0.0800 1.78 0.502 -0.0800 0.78 0.394 -0.0800 -0.13 0.289 -0.0800 -1.39 0.170 -0.0800 -2.49 0.075 -0.0800 -3.45 -0.016 -0.0800 -4.36 -0.098 -0.0800 -5.29 -0.182 -0.0800 -6.45 -0.312 -0.0800 Tabulated from data in file CL00720.DAT & reduced using program Q02.00L File 7075at3.lft created on 09-12-1997 at 13:46:18 using program FORMAT :::::::::::::: 7075ATF1.LFT :::::::::::::: Airfoil: S7075 (A) Builder: J. Robertson Comment: flap = 10 degs: Zig-Zag trip type "D" @ x/c = 68% (h/c = 0.25%) Number of Reynolds #'s: 4 Average Reynolds #: 60500 Number of angles of attack: 49 alpha / Cl / Cm -6.14 -0.041 -0.1200 -4.67 0.140 -0.1200 -3.64 0.231 -0.1200 -2.63 0.299 -0.1200 -1.64 0.390 -0.1200 -0.66 0.477 -0.1200 0.48 0.572 -0.1200 1.50 0.649 -0.1200 2.52 0.707 -0.1200 3.59 1.019 -0.1200 4.47 1.151 -0.1200 5.45 1.232 -0.1200 6.67 1.238 -0.1200 7.53 1.265 -0.1200 8.51 1.296 -0.1200 9.70 1.343 -0.1200 10.58 1.363 -0.1200 11.65 1.333 -0.1200 12.46 1.173 -0.1200 13.58 1.123 -0.1200 14.50 1.145 -0.1200 15.60 1.127 -0.1200 16.55 1.094 -0.1200 17.45 1.116 -0.1200 18.56 1.147 -0.1200 17.02 1.091 -0.1200 16.18 1.102 -0.1200 15.08 1.107 -0.1200 14.01 1.152 -0.1200 13.17 1.139 -0.1200 12.04 1.176 -0.1200 11.08 1.378 -0.1200 10.10 1.362 -0.1200 9.01 1.323 -0.1200 8.15 1.290 -0.1200 7.04 1.254 -0.1200 6.15 1.243 -0.1200 5.21 1.229 -0.1200 4.06 1.142 -0.1200 3.08 0.814 -0.1200 1.94 0.663 -0.1200 0.84 0.604 -0.1200 0.03 0.542 -0.1200 -1.12 0.438 -0.1200 -2.21 0.339 -0.1200 -3.05 0.271 -0.1200 -4.09 0.201 -0.1200 -5.08 0.097 -0.1200 -6.05 -0.025 -0.1200 Tabulated from data in file CL00743.DAT & reduced using program Q02.00L Average Reynolds #: 100300 Number of angles of attack: 49 alpha / Cl / Cm -6.25 -0.040 -0.1200 -4.59 0.145 -0.1200 -3.70 0.227 -0.1200 -2.67 0.322 -0.1200 -1.66 0.396 -0.1200 -0.72 0.498 -0.1200 0.48 0.601 -0.1200 1.34 0.650 -0.1200 2.56 0.868 -0.1200 3.53 1.100 -0.1200 4.63 1.184 -0.1200 5.69 1.225 -0.1200 6.66 1.278 -0.1200 7.65 1.286 -0.1200 8.62 1.313 -0.1200 9.71 1.355 -0.1200 10.67 1.383 -0.1200 11.59 1.380 -0.1200 12.39 1.208 -0.1200 13.49 1.157 -0.1200 14.46 1.172 -0.1200 15.64 1.142 -0.1200 16.71 1.135 -0.1200 17.48 1.100 -0.1200 18.65 1.121 -0.1200 17.02 1.110 -0.1200 16.07 1.167 -0.1200 15.13 1.218 -0.1200 14.06 1.167 -0.1200 13.14 1.184 -0.1200 12.02 1.316 -0.1200 11.06 1.396 -0.1200 9.96 1.351 -0.1200 9.08 1.319 -0.1200 8.18 1.289 -0.1200 6.99 1.258 -0.1200 6.05 1.221 -0.1200 5.10 1.174 -0.1200 3.91 1.118 -0.1200 2.91 0.942 -0.1200 1.89 0.693 -0.1200 0.97 0.617 -0.1200 0.03 0.553 -0.1200 -1.16 0.440 -0.1200 -2.04 0.350 -0.1200 -3.20 0.254 -0.1200 -4.10 0.180 -0.1200 -5.23 0.075 -0.1200 -6.24 -0.028 -0.1200 Tabulated from data in file CL00745.DAT & reduced using program Q02.00L Average Reynolds #: 200100 Number of angles of attack: 49 alpha / Cl / Cm -6.10 0.207 -0.1200 -4.64 0.342 -0.1200 -3.77 0.430 -0.1200 -2.64 0.537 -0.1200 -1.52 0.637 -0.1200 -0.80 0.711 -0.1200 0.50 0.818 -0.1200 1.36 0.900 -0.1200 2.35 1.042 -0.1200 3.54 1.150 -0.1200 4.59 1.174 -0.1200 5.39 1.201 -0.1200 6.50 1.252 -0.1200 7.51 1.291 -0.1200 8.51 1.332 -0.1200 9.58 1.377 -0.1200 10.53 1.405 -0.1200 11.55 1.414 -0.1200 12.40 1.352 -0.1200 13.42 1.265 -0.1200 14.51 1.179 -0.1200 15.51 1.164 -0.1200 16.41 1.161 -0.1200 17.43 1.108 -0.1200 18.37 1.128 -0.1200 17.00 1.114 -0.1200 15.98 1.173 -0.1200 14.99 1.174 -0.1200 13.97 1.189 -0.1200 13.12 1.304 -0.1200 12.06 1.380 -0.1200 11.31 1.413 -0.1200 10.14 1.391 -0.1200 9.16 1.356 -0.1200 8.20 1.314 -0.1200 7.20 1.272 -0.1200 6.16 1.231 -0.1200 5.09 1.184 -0.1200 4.03 1.155 -0.1200 3.13 1.119 -0.1200 1.96 0.990 -0.1200 0.94 0.853 -0.1200 0.03 0.775 -0.1200 -0.97 0.682 -0.1200 -2.13 0.578 -0.1200 -3.10 0.489 -0.1200 -4.34 0.369 -0.1200 -5.38 0.265 -0.1200 -6.49 0.168 -0.1200 Tabulated from data in file CL00747.DAT & reduced using program Q02.00L Average Reynolds #: 299800 Number of angles of attack: 49 alpha / Cl / Cm -6.16 0.199 -0.1200 -4.82 0.357 -0.1200 -3.80 0.463 -0.1200 -2.88 0.559 -0.1200 -1.79 0.664 -0.1200 -0.77 0.760 -0.1200 0.29 0.863 -0.1200 1.44 0.973 -0.1200 2.39 1.080 -0.1200 3.53 1.124 -0.1200 4.45 1.146 -0.1200 5.65 1.199 -0.1200 6.43 1.238 -0.1200 7.41 1.289 -0.1200 8.51 1.346 -0.1200 9.65 1.396 -0.1200 10.52 1.422 -0.1200 11.59 1.433 -0.1200 12.24 1.420 -0.1200 13.38 1.309 -0.1200 14.40 1.221 -0.1200 15.30 1.188 -0.1200 16.30 1.121 -0.1200 17.27 1.128 -0.1200 18.22 1.149 -0.1200 17.14 1.120 -0.1200 16.12 1.140 -0.1200 15.15 1.190 -0.1200 14.09 1.253 -0.1200 13.23 1.317 -0.1200 12.16 1.415 -0.1200 11.03 1.428 -0.1200 10.04 1.407 -0.1200 8.94 1.363 -0.1200 8.04 1.321 -0.1200 7.01 1.265 -0.1200 5.96 1.210 -0.1200 4.96 1.161 -0.1200 4.05 1.129 -0.1200 3.04 1.103 -0.1200 2.02 1.036 -0.1200 1.04 0.932 -0.1200 -0.11 0.823 -0.1200 -1.05 0.732 -0.1200 -1.96 0.645 -0.1200 -3.07 0.537 -0.1200 -4.03 0.438 -0.1200 -5.06 0.328 -0.1200 -6.13 0.199 -0.1200 Tabulated from data in file CL00749.DAT & reduced using program Q02.00L File 7075atf1.lft created on 09-12-1997 at 13:46:18 using program FORMAT :::::::::::::: 7075ATF5.LFT :::::::::::::: Airfoil: S7075 (A) Builder: J. Robertson Comment: flap = 5 degs: Zig-Zag trip type "D" @ x/c = 68% (h/c = 0.25%) Number of Reynolds #'s: 4 Average Reynolds #: 59800 Number of angles of attack: 49 alpha / Cl / Cm -6.24 -0.233 -0.1000 -4.87 -0.057 -0.1000 -3.73 0.048 -0.1000 -2.70 0.131 -0.1000 -1.77 0.195 -0.1000 -0.76 0.288 -0.1000 0.25 0.377 -0.1000 1.29 0.476 -0.1000 2.34 0.537 -0.1000 3.43 0.764 -0.1000 4.54 0.968 -0.1000 5.50 1.000 -0.1000 6.45 1.078 -0.1000 7.50 1.132 -0.1000 8.51 1.165 -0.1000 9.60 1.199 -0.1000 10.65 1.235 -0.1000 11.47 1.254 -0.1000 12.48 1.134 -0.1000 13.51 1.014 -0.1000 14.50 1.052 -0.1000 15.44 1.042 -0.1000 16.58 0.996 -0.1000 17.43 0.992 -0.1000 18.47 0.997 -0.1000 17.14 1.019 -0.1000 16.22 1.021 -0.1000 15.07 1.050 -0.1000 14.18 1.050 -0.1000 13.03 1.062 -0.1000 12.15 1.161 -0.1000 11.24 1.255 -0.1000 10.03 1.222 -0.1000 9.08 1.192 -0.1000 8.16 1.158 -0.1000 7.19 1.126 -0.1000 6.19 1.069 -0.1000 5.19 1.003 -0.1000 4.02 0.903 -0.1000 3.08 0.685 -0.1000 2.11 0.536 -0.1000 0.97 0.453 -0.1000 0.04 0.357 -0.1000 -1.09 0.263 -0.1000 -1.99 0.181 -0.1000 -3.06 0.110 -0.1000 -4.05 0.021 -0.1000 -5.21 -0.112 -0.1000 -6.12 -0.213 -0.1000 Tabulated from data in file CL00735.DAT & reduced using program Q02.00L Average Reynolds #: 100100 Number of angles of attack: 49 alpha / Cl / Cm -6.17 -0.068 -0.1000 -4.79 0.049 -0.1000 -3.80 0.133 -0.1000 -2.78 0.221 -0.1000 -1.76 0.307 -0.1000 -0.79 0.371 -0.1000 0.43 0.476 -0.1000 1.42 0.563 -0.1000 2.31 0.674 -0.1000 3.49 0.925 -0.1000 4.53 1.024 -0.1000 5.61 1.084 -0.1000 6.53 1.151 -0.1000 7.53 1.204 -0.1000 8.51 1.225 -0.1000 9.52 1.255 -0.1000 10.59 1.289 -0.1000 11.66 1.309 -0.1000 12.46 1.246 -0.1000 13.58 1.128 -0.1000 14.58 1.112 -0.1000 15.46 1.106 -0.1000 16.58 1.064 -0.1000 17.46 1.042 -0.1000 18.52 1.077 -0.1000 17.03 1.065 -0.1000 16.11 1.081 -0.1000 15.05 1.121 -0.1000 14.03 1.099 -0.1000 13.24 1.158 -0.1000 12.14 1.312 -0.1000 11.14 1.308 -0.1000 10.19 1.279 -0.1000 9.25 1.241 -0.1000 8.15 1.212 -0.1000 7.12 1.176 -0.1000 6.01 1.097 -0.1000 5.04 1.040 -0.1000 4.15 0.980 -0.1000 3.03 0.831 -0.1000 2.10 0.618 -0.1000 0.98 0.526 -0.1000 -0.03 0.435 -0.1000 -1.03 0.342 -0.1000 -2.04 0.270 -0.1000 -3.03 0.212 -0.1000 -4.14 0.114 -0.1000 -5.11 0.028 -0.1000 -6.11 -0.051 -0.1000 Tabulated from data in file CL00737.DAT & reduced using program Q02.00L Average Reynolds #: 200200 Number of angles of attack: 49 alpha / Cl / Cm -6.14 -0.029 -0.1000 -4.79 0.098 -0.1000 -3.68 0.207 -0.1000 -2.70 0.298 -0.1000 -1.61 0.394 -0.1000 -0.51 0.499 -0.1000 0.51 0.609 -0.1000 1.30 0.709 -0.1000 2.51 0.852 -0.1000 3.39 0.936 -0.1000 4.46 1.021 -0.1000 5.57 1.094 -0.1000 6.67 1.163 -0.1000 7.56 1.203 -0.1000 8.59 1.238 -0.1000 9.51 1.270 -0.1000 10.62 1.303 -0.1000 11.61 1.320 -0.1000 12.53 1.314 -0.1000 13.44 1.224 -0.1000 14.57 1.102 -0.1000 15.42 1.106 -0.1000 16.39 1.070 -0.1000 17.47 1.034 -0.1000 18.39 1.035 -0.1000 16.83 1.049 -0.1000 16.03 1.103 -0.1000 14.85 1.098 -0.1000 14.01 1.166 -0.1000 13.16 1.261 -0.1000 12.20 1.318 -0.1000 11.08 1.311 -0.1000 10.28 1.290 -0.1000 9.06 1.250 -0.1000 8.03 1.209 -0.1000 7.07 1.176 -0.1000 6.05 1.115 -0.1000 5.00 1.047 -0.1000 3.93 0.975 -0.1000 3.07 0.896 -0.1000 1.97 0.784 -0.1000 1.01 0.657 -0.1000 -0.05 0.539 -0.1000 -1.16 0.428 -0.1000 -2.21 0.331 -0.1000 -3.25 0.238 -0.1000 -4.19 0.152 -0.1000 -5.32 0.047 -0.1000 -6.23 -0.037 -0.1000 Tabulated from data in file CL00739.DAT & reduced using program Q02.00L Average Reynolds #: 300500 Number of angles of attack: 49 alpha / Cl / Cm -6.12 -0.020 -0.1000 -4.71 0.113 -0.1000 -3.82 0.189 -0.1000 -2.80 0.294 -0.1000 -1.87 0.403 -0.1000 -0.79 0.511 -0.1000 0.27 0.620 -0.1000 1.30 0.732 -0.1000 2.45 0.856 -0.1000 3.37 0.939 -0.1000 4.45 1.019 -0.1000 5.43 1.088 -0.1000 6.45 1.152 -0.1000 7.56 1.207 -0.1000 8.47 1.248 -0.1000 9.60 1.288 -0.1000 10.64 1.320 -0.1000 11.65 1.336 -0.1000 12.68 1.333 -0.1000 13.42 1.276 -0.1000 14.37 1.190 -0.1000 15.36 1.147 -0.1000 16.37 1.087 -0.1000 17.32 1.046 -0.1000 18.40 1.038 -0.1000 17.11 1.042 -0.1000 16.17 1.098 -0.1000 15.15 1.138 -0.1000 14.26 1.213 -0.1000 13.09 1.303 -0.1000 12.08 1.332 -0.1000 11.03 1.324 -0.1000 9.99 1.297 -0.1000 9.15 1.269 -0.1000 7.97 1.221 -0.1000 7.08 1.182 -0.1000 6.03 1.123 -0.1000 4.96 1.052 -0.1000 3.95 0.978 -0.1000 3.02 0.908 -0.1000 1.88 0.793 -0.1000 0.76 0.670 -0.1000 -0.12 0.574 -0.1000 -1.20 0.467 -0.1000 -2.28 0.359 -0.1000 -3.21 0.250 -0.1000 -4.10 0.161 -0.1000 -5.26 0.062 -0.1000 -6.30 -0.034 -0.1000 Tabulated from data in file CL00741.DAT & reduced using program Q02.00L File 7075atf5.lft created on 09-12-1997 at 13:46:18 using program FORMAT :::::::::::::: 7075BT2.LFT :::::::::::::: Airfoil: S7075 (B) Builder: J. Robertson Comment: Zig-Zag trip type "D" @ x/c = 68% (h/c = 0.25%) Number of Reynolds #'s: 4 Average Reynolds #: 60500 Number of angles of attack: 49 alpha / Cl / Cm -6.34 -0.358 -0.0800 -4.74 -0.245 -0.0800 -3.99 -0.195 -0.0800 -2.76 -0.099 -0.0800 -1.82 -0.026 -0.0800 -0.89 0.059 -0.0800 0.29 0.171 -0.0800 1.22 0.299 -0.0800 2.17 0.459 -0.0800 3.39 0.616 -0.0800 4.43 0.709 -0.0800 5.42 0.788 -0.0800 6.42 0.870 -0.0800 7.45 0.952 -0.0800 8.40 1.007 -0.0800 9.37 1.065 -0.0800 10.58 1.123 -0.0800 11.49 1.145 -0.0800 12.36 1.010 -0.0800 13.49 0.919 -0.0800 14.46 0.934 -0.0800 15.44 0.939 -0.0800 16.43 0.969 -0.0800 17.51 0.987 -0.0800 18.49 1.028 -0.0800 16.90 1.001 -0.0800 15.82 1.004 -0.0800 14.72 0.947 -0.0800 13.88 0.939 -0.0800 12.80 0.953 -0.0800 12.00 1.165 -0.0800 10.99 1.147 -0.0800 9.91 1.107 -0.0800 8.88 1.046 -0.0800 7.83 0.982 -0.0800 6.74 0.905 -0.0800 5.92 0.843 -0.0800 4.81 0.751 -0.0800 3.72 0.653 -0.0800 2.73 0.547 -0.0800 1.69 0.394 -0.0800 0.66 0.231 -0.0800 -0.34 0.116 -0.0800 -1.32 0.025 -0.0800 -2.33 -0.057 -0.0800 -3.37 -0.146 -0.0800 -4.43 -0.222 -0.0800 -5.46 -0.293 -0.0800 -6.50 -0.373 -0.0800 Tabulated from data in file CL00936.DAT & reduced using program Q02.00L Average Reynolds #: 100400 Number of angles of attack: 49 alpha / Cl / Cm -6.37 -0.374 -0.0800 -4.89 -0.202 -0.0800 -3.90 -0.107 -0.0800 -2.94 -0.021 -0.0800 -1.72 0.065 -0.0800 -0.79 0.125 -0.0800 0.17 0.260 -0.0800 1.38 0.419 -0.0800 2.37 0.520 -0.0800 3.34 0.604 -0.0800 4.48 0.709 -0.0800 5.23 0.772 -0.0800 6.55 0.889 -0.0800 7.54 0.963 -0.0800 8.52 1.024 -0.0800 9.46 1.079 -0.0800 10.38 1.125 -0.0800 11.56 1.154 -0.0800 12.43 1.156 -0.0800 13.53 0.974 -0.0800 14.36 0.955 -0.0800 15.45 0.988 -0.0800 16.42 0.959 -0.0800 17.57 0.945 -0.0800 18.32 0.956 -0.0800 16.87 0.941 -0.0800 15.72 0.961 -0.0800 14.89 0.921 -0.0800 13.77 0.961 -0.0800 12.86 0.983 -0.0800 11.88 1.163 -0.0800 10.77 1.134 -0.0800 9.90 1.098 -0.0800 8.82 1.033 -0.0800 7.70 0.964 -0.0800 6.85 0.902 -0.0800 5.71 0.804 -0.0800 4.86 0.729 -0.0800 3.72 0.623 -0.0800 2.63 0.526 -0.0800 1.83 0.451 -0.0800 0.72 0.322 -0.0800 -0.53 0.151 -0.0800 -1.30 0.073 -0.0800 -2.57 -0.000 -0.0800 -3.39 -0.069 -0.0800 -4.43 -0.166 -0.0800 -5.56 -0.271 -0.0800 -6.40 -0.370 -0.0800 Tabulated from data in file CL00938.DAT & reduced using program Q02.00L Average Reynolds #: 200800 Number of angles of attack: 49 alpha / Cl / Cm -6.07 -0.345 -0.0800 -4.87 -0.208 -0.0800 -3.76 -0.108 -0.0800 -2.76 -0.014 -0.0800 -1.68 0.090 -0.0800 -0.88 0.165 -0.0800 0.18 0.286 -0.0800 1.22 0.392 -0.0800 2.39 0.510 -0.0800 3.38 0.616 -0.0800 4.40 0.711 -0.0800 5.45 0.810 -0.0800 6.49 0.903 -0.0800 7.48 0.978 -0.0800 8.49 1.048 -0.0800 9.50 1.117 -0.0800 10.43 1.165 -0.0800 11.35 1.185 -0.0800 12.49 1.180 -0.0800 13.36 1.170 -0.0800 14.18 1.049 -0.0800 15.40 0.993 -0.0800 16.58 0.986 -0.0800 17.50 0.983 -0.0800 18.58 0.968 -0.0800 16.70 0.968 -0.0800 15.67 0.997 -0.0800 14.69 1.103 -0.0800 14.00 1.075 -0.0800 13.03 1.176 -0.0800 11.90 1.186 -0.0800 10.91 1.176 -0.0800 9.79 1.126 -0.0800 8.73 1.057 -0.0800 7.90 0.997 -0.0800 6.78 0.915 -0.0800 5.68 0.819 -0.0800 4.84 0.740 -0.0800 3.62 0.626 -0.0800 2.78 0.539 -0.0800 1.55 0.414 -0.0800 0.64 0.326 -0.0800 -0.47 0.201 -0.0800 -1.40 0.111 -0.0800 -2.36 0.017 -0.0800 -3.61 -0.099 -0.0800 -4.55 -0.186 -0.0800 -5.55 -0.278 -0.0800 -6.37 -0.381 -0.0800 Tabulated from data in file CL00940.DAT & reduced using program Q02.00L Average Reynolds #: 301600 Number of angles of attack: 49 alpha / Cl / Cm -6.49 -0.399 -0.0800 -4.89 -0.217 -0.0800 -3.74 -0.107 -0.0800 -2.79 -0.018 -0.0800 -1.51 0.107 -0.0800 -0.72 0.186 -0.0800 0.19 0.275 -0.0800 1.50 0.419 -0.0800 2.35 0.510 -0.0800 3.47 0.628 -0.0800 4.29 0.708 -0.0800 5.35 0.809 -0.0800 6.40 0.903 -0.0800 7.43 0.985 -0.0800 8.44 1.064 -0.0800 9.45 1.138 -0.0800 10.43 1.195 -0.0800 11.64 1.219 -0.0800 12.51 1.219 -0.0800 13.35 1.208 -0.0800 14.31 1.145 -0.0800 15.43 1.088 -0.0800 16.40 1.063 -0.0800 17.46 1.019 -0.0800 18.28 0.998 -0.0800 16.69 1.042 -0.0800 15.75 1.088 -0.0800 14.64 1.116 -0.0800 13.94 1.178 -0.0800 12.80 1.214 -0.0800 11.77 1.217 -0.0800 10.85 1.204 -0.0800 9.84 1.159 -0.0800 8.72 1.080 -0.0800 7.91 1.018 -0.0800 6.74 0.924 -0.0800 5.82 0.845 -0.0800 4.71 0.741 -0.0800 3.73 0.646 -0.0800 2.76 0.546 -0.0800 1.74 0.436 -0.0800 0.49 0.304 -0.0800 -0.52 0.196 -0.0800 -1.27 0.128 -0.0800 -2.38 0.019 -0.0800 -3.46 -0.085 -0.0800 -4.57 -0.191 -0.0800 -5.72 -0.301 -0.0800 -6.58 -0.409 -0.0800 Tabulated from data in file CL00942.DAT & reduced using program Q02.00L File 7075bt2.lft created on 09-12-1997 at 13:46:18 using program FORMAT :::::::::::::: CR001.LFT :::::::::::::: Airfoil: CR-001 Builder: J. Robertson Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60100 Number of angles of attack: 49 alpha / Cl / Cm -6.37 -0.332 -0.1200 -5.00 -0.226 -0.1200 -4.08 -0.107 -0.1200 -2.97 -0.002 -0.1200 -1.94 0.106 -0.1200 -0.84 0.209 -0.1200 0.22 0.321 -0.1200 1.07 0.406 -0.1200 2.21 0.553 -0.1200 3.28 0.720 -0.1200 4.21 0.862 -0.1200 5.38 0.956 -0.1200 6.35 1.035 -0.1200 7.30 1.107 -0.1200 8.44 1.165 -0.1200 9.36 1.210 -0.1200 10.46 1.250 -0.1200 11.33 1.268 -0.1200 12.37 1.140 -0.1200 13.21 1.147 -0.1200 14.21 1.114 -0.1200 15.25 1.087 -0.1200 16.37 1.081 -0.1200 17.32 1.110 -0.1200 18.25 1.115 -0.1200 16.88 1.114 -0.1200 15.85 1.119 -0.1200 14.86 1.107 -0.1200 13.81 1.101 -0.1200 12.90 1.152 -0.1200 11.98 1.271 -0.1200 10.93 1.262 -0.1200 9.98 1.231 -0.1200 8.97 1.182 -0.1200 7.83 1.128 -0.1200 6.83 1.060 -0.1200 5.80 0.983 -0.1200 4.76 0.896 -0.1200 3.76 0.784 -0.1200 2.76 0.626 -0.1200 1.76 0.506 -0.1200 0.74 0.378 -0.1200 -0.27 0.278 -0.1200 -1.45 0.162 -0.1200 -2.39 0.071 -0.1200 -3.40 -0.024 -0.1200 -4.48 -0.145 -0.1200 -5.55 -0.256 -0.1200 -6.48 -0.302 -0.1200 Tabulated from data in file CL00657.DAT & reduced using program Q02.00L Average Reynolds #: 100100 Number of angles of attack: 49 alpha / Cl / Cm -6.35 -0.366 -0.1200 -5.07 -0.284 -0.1200 -4.03 -0.130 -0.1200 -2.93 0.015 -0.1200 -2.06 0.110 -0.1200 -0.96 0.227 -0.1200 0.09 0.373 -0.1200 1.22 0.540 -0.1200 2.12 0.665 -0.1200 3.23 0.792 -0.1200 4.41 0.897 -0.1200 5.35 0.982 -0.1200 6.30 1.060 -0.1200 7.23 1.132 -0.1200 8.31 1.196 -0.1200 9.41 1.244 -0.1200 10.28 1.272 -0.1200 11.32 1.290 -0.1200 12.39 1.281 -0.1200 13.35 1.199 -0.1200 14.44 1.115 -0.1200 15.27 1.133 -0.1200 16.34 1.097 -0.1200 17.28 1.104 -0.1200 18.49 1.086 -0.1200 16.80 1.092 -0.1200 15.91 1.074 -0.1200 14.88 1.109 -0.1200 13.84 1.111 -0.1200 12.93 1.199 -0.1200 11.98 1.275 -0.1200 10.90 1.267 -0.1200 9.79 1.243 -0.1200 8.94 1.203 -0.1200 7.90 1.155 -0.1200 6.84 1.077 -0.1200 5.75 0.990 -0.1200 4.86 0.912 -0.1200 3.78 0.819 -0.1200 2.74 0.717 -0.1200 1.69 0.586 -0.1200 0.63 0.440 -0.1200 -0.43 0.276 -0.1200 -1.28 0.181 -0.1200 -2.51 0.051 -0.1200 -3.52 -0.063 -0.1200 -4.40 -0.188 -0.1200 -5.46 -0.314 -0.1200 -6.51 -0.368 -0.1200 Tabulated from data in file CL00659.DAT & reduced using program Q02.00L Average Reynolds #: 200300 Number of angles of attack: 49 alpha / Cl / Cm -6.42 -0.387 -0.1200 -4.93 -0.253 -0.1200 -3.98 -0.079 -0.1200 -2.99 0.068 -0.1200 -1.74 0.244 -0.1200 -0.85 0.376 -0.1200 0.11 0.493 -0.1200 1.27 0.613 -0.1200 2.28 0.711 -0.1200 3.28 0.809 -0.1200 4.28 0.902 -0.1200 5.20 0.986 -0.1200 6.48 1.092 -0.1200 7.46 1.160 -0.1200 8.43 1.214 -0.1200 9.39 1.259 -0.1200 10.31 1.287 -0.1200 11.33 1.296 -0.1200 12.39 1.273 -0.1200 13.43 1.254 -0.1200 14.30 1.202 -0.1200 15.25 1.175 -0.1200 16.17 1.137 -0.1200 17.32 1.100 -0.1200 18.27 1.097 -0.1200 16.60 1.110 -0.1200 15.71 1.168 -0.1200 14.65 1.208 -0.1200 13.80 1.250 -0.1200 12.92 1.263 -0.1200 11.85 1.291 -0.1200 10.88 1.295 -0.1200 9.86 1.271 -0.1200 8.78 1.224 -0.1200 7.74 1.166 -0.1200 6.87 1.109 -0.1200 5.89 1.033 -0.1200 4.67 0.925 -0.1200 3.66 0.831 -0.1200 2.64 0.728 -0.1200 1.59 0.632 -0.1200 0.61 0.534 -0.1200 -0.49 0.405 -0.1200 -1.52 0.266 -0.1200 -2.56 0.118 -0.1200 -3.65 -0.034 -0.1200 -4.46 -0.173 -0.1200 -5.49 -0.326 -0.1200 -6.50 -0.390 -0.1200 Tabulated from data in file CL00661.DAT & reduced using program Q02.00L Average Reynolds #: 300700 Number of angles of attack: 49 alpha / Cl / Cm -6.47 -0.387 -0.1200 -5.17 -0.216 -0.1200 -3.98 0.003 -0.1200 -3.10 0.130 -0.1200 -1.97 0.285 -0.1200 -1.02 0.390 -0.1200 0.01 0.490 -0.1200 1.18 0.610 -0.1200 2.23 0.717 -0.1200 3.21 0.814 -0.1200 4.25 0.915 -0.1200 5.16 0.997 -0.1200 6.46 1.104 -0.1200 7.29 1.163 -0.1200 8.51 1.240 -0.1200 9.60 1.296 -0.1200 10.36 1.317 -0.1200 11.35 1.322 -0.1200 12.52 1.299 -0.1200 13.31 1.275 -0.1200 13.97 1.291 -0.1200 15.08 1.232 -0.1200 16.00 1.170 -0.1200 17.05 1.139 -0.1200 18.06 1.122 -0.1200 16.93 1.133 -0.1200 15.94 1.182 -0.1200 15.01 1.235 -0.1200 14.11 1.298 -0.1200 13.11 1.280 -0.1200 11.92 1.309 -0.1200 10.78 1.316 -0.1200 9.76 1.291 -0.1200 8.77 1.244 -0.1200 7.70 1.176 -0.1200 6.78 1.111 -0.1200 5.63 1.022 -0.1200 4.54 0.928 -0.1200 3.77 0.855 -0.1200 2.57 0.738 -0.1200 1.70 0.651 -0.1200 0.58 0.534 -0.1200 -0.24 0.457 -0.1200 -1.44 0.335 -0.1200 -2.36 0.224 -0.1200 -3.44 0.075 -0.1200 -4.55 -0.099 -0.1200 -5.42 -0.270 -0.1200 -6.51 -0.393 -0.1200 Tabulated from data in file CL00663.DAT & reduced using program Q02.00L File cr001.lft created on 09-12-1997 at 13:46:17 using program FORMAT :::::::::::::: DAVIS3R.LFT :::::::::::::: Airfoil: Davis 3R Builder: H. Cole Comment: multiple plain trips (h/c = 0.15%; w/c = 2.1%) @ x/c = 28.1%; 42.4%; 54.4%; 65.4%; 76.3% Number of Reynolds #'s: 5 Average Reynolds #: 39800 Number of angles of attack: 49 alpha / Cl / Cm -3.18 -0.167 -0.1700 -1.63 0.187 -0.1700 -0.72 0.314 -0.1700 0.40 0.446 -0.1700 1.31 0.551 -0.1700 2.38 0.669 -0.1700 3.50 0.781 -0.1700 4.39 0.845 -0.1700 5.50 0.926 -0.1700 6.44 1.075 -0.1700 7.55 1.147 -0.1700 8.45 1.184 -0.1700 9.54 1.217 -0.1700 10.62 1.262 -0.1700 11.70 1.304 -0.1700 12.53 1.312 -0.1700 13.56 1.324 -0.1700 14.55 1.295 -0.1700 15.53 1.268 -0.1700 16.50 1.244 -0.1700 17.47 1.171 -0.1700 18.45 1.162 -0.1700 19.66 1.134 -0.1700 20.52 1.143 -0.1700 21.46 1.176 -0.1700 19.99 1.165 -0.1700 19.07 1.150 -0.1700 17.88 1.124 -0.1700 17.01 1.127 -0.1700 16.08 1.155 -0.1700 14.91 1.225 -0.1700 14.01 1.284 -0.1700 13.11 1.283 -0.1700 11.95 1.275 -0.1700 11.02 1.245 -0.1700 10.06 1.204 -0.1700 9.08 1.168 -0.1700 8.07 1.121 -0.1700 7.09 1.077 -0.1700 5.84 0.939 -0.1700 4.90 0.838 -0.1700 3.97 0.734 -0.1700 2.76 0.647 -0.1700 1.83 0.549 -0.1700 0.91 0.430 -0.1700 -0.29 0.291 -0.1700 -1.18 0.176 -0.1700 -2.15 -0.000 -0.1700 -3.29 -0.223 -0.1700 Tabulated from data in file CL00751.DAT & reduced using program Q02.00L Average Reynolds #: 59600 Number of angles of attack: 49 alpha / Cl / Cm -3.14 -0.026 -0.1700 -1.58 0.262 -0.1700 -0.59 0.396 -0.1700 0.36 0.510 -0.1700 1.48 0.646 -0.1700 2.37 0.746 -0.1700 3.46 0.854 -0.1700 4.59 0.951 -0.1700 5.54 1.042 -0.1700 6.45 1.099 -0.1700 7.51 1.156 -0.1700 8.56 1.180 -0.1700 9.50 1.222 -0.1700 10.62 1.270 -0.1700 11.70 1.310 -0.1700 12.57 1.323 -0.1700 13.64 1.310 -0.1700 14.47 1.271 -0.1700 15.57 1.146 -0.1700 16.46 1.062 -0.1700 17.53 1.106 -0.1700 18.59 1.141 -0.1700 19.72 1.155 -0.1700 20.46 1.138 -0.1700 21.56 1.176 -0.1700 20.02 1.153 -0.1700 18.99 1.132 -0.1700 17.99 1.124 -0.1700 17.01 1.121 -0.1700 16.05 1.141 -0.1700 15.09 1.242 -0.1700 14.13 1.288 -0.1700 13.07 1.334 -0.1700 12.06 1.322 -0.1700 11.06 1.286 -0.1700 10.06 1.243 -0.1700 9.03 1.193 -0.1700 8.00 1.155 -0.1700 6.98 1.123 -0.1700 6.00 1.057 -0.1700 4.99 0.970 -0.1700 3.97 0.878 -0.1700 2.95 0.780 -0.1700 1.93 0.676 -0.1700 0.93 0.576 -0.1700 -0.33 0.413 -0.1700 -1.25 0.302 -0.1700 -2.21 0.144 -0.1700 -3.23 -0.039 -0.1700 Tabulated from data in file CL00753.DAT & reduced using program Q02.00L Average Reynolds #: 99800 Number of angles of attack: 49 alpha / Cl / Cm -3.11 0.105 -0.1700 -1.56 0.382 -0.1700 -0.53 0.502 -0.1700 0.51 0.610 -0.1700 1.51 0.712 -0.1700 2.52 0.810 -0.1700 3.50 0.903 -0.1700 4.47 0.993 -0.1700 5.67 1.092 -0.1700 6.66 1.145 -0.1700 7.66 1.188 -0.1700 8.64 1.233 -0.1700 9.61 1.278 -0.1700 10.53 1.316 -0.1700 11.72 1.353 -0.1700 12.59 1.365 -0.1700 13.69 1.328 -0.1700 14.61 1.279 -0.1700 15.67 1.168 -0.1700 16.63 1.160 -0.1700 17.69 1.150 -0.1700 18.68 1.152 -0.1700 19.43 1.169 -0.1700 20.49 1.179 -0.1700 21.53 1.193 -0.1700 20.05 1.176 -0.1700 18.76 1.163 -0.1700 17.98 1.169 -0.1700 16.86 1.153 -0.1700 16.10 1.174 -0.1700 14.88 1.210 -0.1700 13.92 1.367 -0.1700 12.97 1.352 -0.1700 12.10 1.346 -0.1700 10.94 1.311 -0.1700 9.89 1.269 -0.1700 9.10 1.230 -0.1700 7.96 1.174 -0.1700 6.88 1.124 -0.1700 5.81 1.069 -0.1700 5.01 1.013 -0.1700 3.88 0.909 -0.1700 2.80 0.801 -0.1700 1.98 0.723 -0.1700 0.84 0.618 -0.1700 -0.26 0.501 -0.1700 -1.33 0.390 -0.1700 -2.13 0.277 -0.1700 -3.24 0.095 -0.1700 Tabulated from data in file CL00755.DAT & reduced using program Q02.00L Average Reynolds #: 199400 Number of angles of attack: 49 alpha / Cl / Cm -2.92 0.052 -0.1700 -2.05 0.170 -0.1700 -1.15 0.329 -0.1700 -0.08 0.596 -0.1700 1.19 0.736 -0.1700 2.05 0.825 -0.1700 3.05 0.928 -0.1700 4.06 1.021 -0.1700 5.24 1.107 -0.1700 6.08 1.153 -0.1700 7.19 1.211 -0.1700 8.16 1.258 -0.1700 9.21 1.304 -0.1700 10.13 1.339 -0.1700 11.10 1.391 -0.1700 12.35 1.429 -0.1700 13.07 1.421 -0.1700 14.10 1.370 -0.1700 15.09 1.325 -0.1700 15.98 1.204 -0.1700 16.92 1.215 -0.1700 18.03 1.169 -0.1700 19.09 1.169 -0.1700 20.06 1.189 -0.1700 21.06 1.212 -0.1700 20.41 1.192 -0.1700 19.46 1.177 -0.1700 18.39 1.174 -0.1700 17.43 1.202 -0.1700 16.43 1.206 -0.1700 15.51 1.188 -0.1700 14.64 1.353 -0.1700 13.47 1.416 -0.1700 12.71 1.422 -0.1700 11.45 1.411 -0.1700 10.46 1.351 -0.1700 9.46 1.309 -0.1700 8.37 1.263 -0.1700 7.41 1.218 -0.1700 6.31 1.158 -0.1700 5.37 1.108 -0.1700 4.16 1.025 -0.1700 3.31 0.947 -0.1700 2.19 0.830 -0.1700 1.15 0.724 -0.1700 0.26 0.627 -0.1700 -0.87 0.499 -0.1700 -1.94 0.184 -0.1700 -2.98 0.044 -0.1700 Tabulated from data in file CL00871.DAT & reduced using program Q02.00L Average Reynolds #: 299200 Number of angles of attack: 49 alpha / Cl / Cm -2.79 0.073 -0.1700 -1.79 0.428 -0.1700 -0.59 0.572 -0.1700 0.43 0.685 -0.1700 1.45 0.792 -0.1700 2.42 0.893 -0.1700 3.65 1.015 -0.1700 4.57 1.081 -0.1700 5.52 1.139 -0.1700 6.57 1.201 -0.1700 7.76 1.262 -0.1700 8.70 1.304 -0.1700 9.76 1.360 -0.1700 10.72 1.432 -0.1700 11.76 1.478 -0.1700 12.81 1.452 -0.1700 13.00 1.421 -0.1700 14.19 1.341 -0.1700 15.31 1.255 -0.1700 16.13 1.169 -0.1700 17.38 1.187 -0.1700 18.29 1.174 -0.1700 19.20 1.155 -0.1700 20.16 1.168 -0.1700 21.22 1.201 -0.1700 20.00 1.180 -0.1700 18.99 1.168 -0.1700 18.35 1.171 -0.1700 17.16 1.179 -0.1700 15.95 1.226 -0.1700 15.16 1.340 -0.1700 14.11 1.385 -0.1700 12.85 1.429 -0.1700 12.67 1.439 -0.1700 10.72 1.429 -0.1700 9.74 1.353 -0.1700 8.84 1.305 -0.1700 7.92 1.262 -0.1700 6.90 1.212 -0.1700 5.77 1.148 -0.1700 4.70 1.084 -0.1700 3.69 1.012 -0.1700 2.74 0.922 -0.1700 1.89 0.832 -0.1700 0.77 0.713 -0.1700 -0.29 0.594 -0.1700 -1.10 0.504 -0.1700 -2.30 0.333 -0.1700 -2.28 0.162 -0.1700 Tabulated from data in file CL00873.DAT & reduced using program Q02.00L File davis3r.lft created on 09-12-1997 at 13:46:17 using program FORMAT :::::::::::::: DU86.LFT :::::::::::::: Airfoil: DU 86-084/18 Builder: R. Adams Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60200 Number of angles of attack: 49 alpha / Cl / Cm -5.90 -0.407 -0.0260 -4.46 -0.333 -0.0260 -3.46 -0.272 -0.0260 -2.42 -0.197 -0.0260 -1.35 -0.118 -0.0260 -0.35 -0.042 -0.0260 0.67 0.058 -0.0260 1.69 0.152 -0.0260 2.73 0.290 -0.0260 3.79 0.473 -0.0260 4.84 0.567 -0.0260 5.85 0.638 -0.0260 6.67 0.691 -0.0260 7.82 0.755 -0.0260 8.91 0.814 -0.0260 9.78 0.860 -0.0260 10.87 0.896 -0.0260 11.72 0.905 -0.0260 12.84 0.899 -0.0260 13.69 0.824 -0.0260 14.81 0.832 -0.0260 15.94 0.857 -0.0260 16.87 0.833 -0.0260 17.97 0.824 -0.0260 18.82 0.821 -0.0260 17.30 0.848 -0.0260 16.35 0.854 -0.0260 15.28 0.883 -0.0260 14.33 0.890 -0.0260 13.37 0.886 -0.0260 12.36 0.901 -0.0260 11.46 0.954 -0.0260 10.39 0.923 -0.0260 9.45 0.883 -0.0260 8.36 0.820 -0.0260 7.40 0.760 -0.0260 6.29 0.701 -0.0260 5.34 0.609 -0.0260 4.25 0.549 -0.0260 3.18 0.389 -0.0260 2.31 0.249 -0.0260 1.24 0.137 -0.0260 0.18 0.037 -0.0260 -0.89 -0.056 -0.0260 -1.97 -0.131 -0.0260 -2.84 -0.214 -0.0260 -3.91 -0.280 -0.0260 -4.97 -0.340 -0.0260 -5.91 -0.393 -0.0260 Tabulated from data in file CL00789.DAT & reduced using program Q02.00L Average Reynolds #: 100600 Number of angles of attack: 49 alpha / Cl / Cm -5.96 -0.460 -0.0260 -4.46 -0.364 -0.0260 -3.38 -0.281 -0.0260 -2.54 -0.215 -0.0260 -1.43 -0.128 -0.0260 -0.33 -0.020 -0.0260 0.68 0.108 -0.0260 1.79 0.249 -0.0260 2.62 0.380 -0.0260 3.75 0.496 -0.0260 4.85 0.577 -0.0260 5.69 0.639 -0.0260 6.88 0.729 -0.0260 7.75 0.789 -0.0260 8.92 0.863 -0.0260 9.77 0.906 -0.0260 10.85 0.950 -0.0260 11.82 0.970 -0.0260 12.91 0.914 -0.0260 13.77 0.883 -0.0260 14.89 0.872 -0.0260 15.91 0.870 -0.0260 16.95 0.862 -0.0260 17.81 0.854 -0.0260 18.98 0.867 -0.0260 17.26 0.845 -0.0260 16.25 0.868 -0.0260 15.35 0.909 -0.0260 14.37 0.869 -0.0260 13.35 0.918 -0.0260 12.41 0.952 -0.0260 11.28 0.955 -0.0260 10.33 0.942 -0.0260 9.44 0.893 -0.0260 8.38 0.835 -0.0260 7.43 0.769 -0.0260 6.29 0.692 -0.0260 5.32 0.618 -0.0260 4.20 0.534 -0.0260 3.29 0.459 -0.0260 2.17 0.313 -0.0260 1.04 0.152 -0.0260 0.08 0.041 -0.0260 -0.85 -0.071 -0.0260 -1.86 -0.164 -0.0260 -2.96 -0.231 -0.0260 -4.02 -0.321 -0.0260 -4.92 -0.383 -0.0260 -5.99 -0.442 -0.0260 Tabulated from data in file CL00791.DAT & reduced using program Q02.00L Average Reynolds #: 201300 Number of angles of attack: 49 alpha / Cl / Cm -5.89 -0.410 -0.0260 -4.44 -0.269 -0.0260 -3.30 -0.159 -0.0260 -2.37 -0.075 -0.0260 -1.42 -0.005 -0.0260 -0.20 0.113 -0.0260 0.70 0.238 -0.0260 1.61 0.313 -0.0260 2.69 0.395 -0.0260 3.79 0.481 -0.0260 4.69 0.572 -0.0260 5.81 0.670 -0.0260 6.93 0.759 -0.0260 7.83 0.826 -0.0260 8.89 0.895 -0.0260 9.79 0.953 -0.0260 10.89 0.992 -0.0260 11.89 1.003 -0.0260 12.98 0.984 -0.0260 13.67 0.925 -0.0260 14.76 0.922 -0.0260 15.84 0.889 -0.0260 16.92 0.882 -0.0260 17.93 0.868 -0.0260 18.97 0.876 -0.0260 17.29 0.866 -0.0260 16.14 0.884 -0.0260 15.17 0.903 -0.0260 14.39 0.927 -0.0260 13.27 0.942 -0.0260 12.25 0.989 -0.0260 11.43 0.998 -0.0260 10.37 0.983 -0.0260 9.34 0.916 -0.0260 8.36 0.854 -0.0260 7.36 0.783 -0.0260 6.35 0.704 -0.0260 5.15 0.600 -0.0260 4.14 0.507 -0.0260 3.28 0.428 -0.0260 2.15 0.343 -0.0260 1.11 0.264 -0.0260 0.05 0.160 -0.0260 -1.06 0.009 -0.0260 -1.92 -0.059 -0.0260 -3.02 -0.143 -0.0260 -3.88 -0.221 -0.0260 -5.09 -0.337 -0.0260 -5.95 -0.417 -0.0260 Tabulated from data in file CL00793.DAT & reduced using program Q02.00L Average Reynolds #: 301600 Number of angles of attack: 49 alpha / Cl / Cm -6.41 -0.474 -0.0260 -4.12 -0.263 -0.0260 -3.35 -0.188 -0.0260 -2.26 -0.090 -0.0260 -1.15 -0.010 -0.0260 -0.46 0.032 -0.0260 0.85 0.209 -0.0260 1.80 0.297 -0.0260 2.65 0.377 -0.0260 3.92 0.495 -0.0260 4.69 0.564 -0.0260 5.92 0.675 -0.0260 6.80 0.749 -0.0260 7.87 0.835 -0.0260 8.91 0.905 -0.0260 9.73 0.966 -0.0260 10.74 1.010 -0.0260 11.72 1.013 -0.0260 12.65 1.013 -0.0260 13.83 0.961 -0.0260 14.89 0.910 -0.0260 15.78 0.894 -0.0260 16.81 0.868 -0.0260 17.74 0.857 -0.0260 18.88 0.868 -0.0260 17.26 0.869 -0.0260 16.18 0.878 -0.0260 15.35 0.892 -0.0260 14.31 0.936 -0.0260 13.21 0.987 -0.0260 12.41 1.013 -0.0260 11.33 1.017 -0.0260 10.40 0.995 -0.0260 9.30 0.929 -0.0260 8.43 0.871 -0.0260 7.25 0.784 -0.0260 6.22 0.697 -0.0260 5.18 0.604 -0.0260 4.14 0.510 -0.0260 3.11 0.413 -0.0260 2.06 0.317 -0.0260 1.17 0.238 -0.0260 0.16 0.102 -0.0260 -0.99 -0.008 -0.0260 -1.95 -0.067 -0.0260 -3.24 -0.179 -0.0260 -3.96 -0.249 -0.0260 -5.22 -0.365 -0.0260 -5.98 -0.432 -0.0260 Tabulated from data in file CL00795.DAT & reduced using program Q02.00L File du86.lft created on 09-12-1997 at 13:46:17 using program FORMAT :::::::::::::: E374B.LFT :::::::::::::: Airfoil: E374 (B) Builder: M. Bame Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60300 Number of angles of attack: 49 alpha / Cl / Cm -6.65 -0.383 -0.0420 -5.36 -0.341 -0.0420 -4.38 -0.299 -0.0420 -3.38 -0.238 -0.0420 -2.35 -0.144 -0.0420 -1.33 -0.038 -0.0420 -0.28 0.111 -0.0420 0.74 0.209 -0.0420 1.74 0.293 -0.0420 2.83 0.363 -0.0420 3.79 0.458 -0.0420 4.86 0.641 -0.0420 5.92 0.753 -0.0420 6.95 0.854 -0.0420 7.92 0.924 -0.0420 8.98 0.949 -0.0420 9.98 0.984 -0.0420 10.95 1.018 -0.0420 11.98 1.039 -0.0420 12.99 1.035 -0.0420 13.98 0.997 -0.0420 14.96 0.871 -0.0420 15.92 0.859 -0.0420 16.92 0.847 -0.0420 17.90 0.823 -0.0420 16.90 0.881 -0.0420 15.93 0.888 -0.0420 14.94 0.926 -0.0420 13.95 0.996 -0.0420 12.96 1.010 -0.0420 11.95 1.029 -0.0420 10.94 1.013 -0.0420 9.94 0.975 -0.0420 8.91 0.940 -0.0420 7.92 0.919 -0.0420 6.91 0.837 -0.0420 5.90 0.742 -0.0420 4.84 0.616 -0.0420 3.80 0.443 -0.0420 2.77 0.345 -0.0420 1.72 0.284 -0.0420 0.72 0.197 -0.0420 -0.28 0.085 -0.0420 -1.32 -0.055 -0.0420 -2.38 -0.158 -0.0420 -3.40 -0.256 -0.0420 -4.42 -0.317 -0.0420 -5.40 -0.362 -0.0420 -6.46 -0.413 -0.0420 Tabulated from data in file CL00615.DAT & reduced using program Q02.00L Average Reynolds #: 100700 Number of angles of attack: 49 alpha / Cl / Cm -6.49 -0.430 -0.0420 -5.28 -0.378 -0.0420 -4.26 -0.279 -0.0420 -3.21 -0.134 -0.0420 -2.21 0.018 -0.0420 -1.23 0.146 -0.0420 -0.10 0.255 -0.0420 0.87 0.331 -0.0420 1.87 0.410 -0.0420 2.88 0.501 -0.0420 3.91 0.605 -0.0420 4.98 0.713 -0.0420 6.06 0.813 -0.0420 7.00 0.895 -0.0420 8.07 0.950 -0.0420 9.10 0.979 -0.0420 10.11 1.016 -0.0420 11.10 1.043 -0.0420 12.06 1.053 -0.0420 13.10 1.046 -0.0420 14.03 0.976 -0.0420 15.01 0.923 -0.0420 16.05 0.888 -0.0420 16.96 0.882 -0.0420 18.05 0.859 -0.0420 16.78 0.874 -0.0420 15.79 0.925 -0.0420 14.78 0.936 -0.0420 13.82 1.008 -0.0420 12.87 1.025 -0.0420 11.89 1.043 -0.0420 10.88 1.028 -0.0420 9.88 0.998 -0.0420 8.90 0.960 -0.0420 7.83 0.928 -0.0420 6.85 0.870 -0.0420 5.77 0.774 -0.0420 4.82 0.683 -0.0420 3.76 0.570 -0.0420 2.72 0.469 -0.0420 1.64 0.371 -0.0420 0.70 0.297 -0.0420 -0.38 0.220 -0.0420 -1.42 0.100 -0.0420 -2.38 -0.034 -0.0420 -3.44 -0.180 -0.0420 -4.52 -0.313 -0.0420 -5.50 -0.387 -0.0420 -6.49 -0.431 -0.0420 Tabulated from data in file CL00617.DAT & reduced using program Q02.00L Average Reynolds #: 201300 Number of angles of attack: 49 alpha / Cl / Cm -6.46 -0.436 -0.0420 -5.26 -0.276 -0.0420 -4.12 -0.150 -0.0420 -3.14 -0.078 -0.0420 -2.16 -0.004 -0.0420 -1.18 0.080 -0.0420 -0.13 0.236 -0.0420 0.92 0.344 -0.0420 1.93 0.437 -0.0420 2.95 0.534 -0.0420 3.99 0.637 -0.0420 5.00 0.737 -0.0420 6.05 0.835 -0.0420 7.15 0.910 -0.0420 8.02 0.942 -0.0420 9.02 0.985 -0.0420 10.11 1.021 -0.0420 11.03 1.043 -0.0420 12.14 1.062 -0.0420 13.13 1.095 -0.0420 14.02 1.056 -0.0420 15.12 0.971 -0.0420 16.09 0.919 -0.0420 17.16 0.900 -0.0420 18.18 0.886 -0.0420 16.69 0.903 -0.0420 15.79 0.932 -0.0420 14.74 0.978 -0.0420 13.83 1.094 -0.0420 12.82 1.086 -0.0420 11.95 1.053 -0.0420 10.92 1.036 -0.0420 9.90 1.012 -0.0420 8.83 0.972 -0.0420 7.84 0.930 -0.0420 6.85 0.891 -0.0420 5.76 0.800 -0.0420 4.70 0.699 -0.0420 3.78 0.607 -0.0420 2.68 0.500 -0.0420 1.64 0.403 -0.0420 0.58 0.306 -0.0420 -0.43 0.169 -0.0420 -1.48 0.048 -0.0420 -2.47 -0.040 -0.0420 -3.56 -0.116 -0.0420 -4.50 -0.192 -0.0420 -5.54 -0.321 -0.0420 -6.63 -0.449 -0.0420 Tabulated from data in file CL00619.DAT & reduced using program Q02.00L Average Reynolds #: 301900 Number of angles of attack: 49 alpha / Cl / Cm -6.40 -0.386 -0.0420 -5.23 -0.256 -0.0420 -4.14 -0.169 -0.0420 -3.22 -0.093 -0.0420 -2.11 -0.006 -0.0420 -1.22 0.068 -0.0420 -0.17 0.185 -0.0420 0.90 0.341 -0.0420 1.96 0.442 -0.0420 2.99 0.539 -0.0420 3.96 0.635 -0.0420 4.92 0.729 -0.0420 6.05 0.831 -0.0420 6.99 0.889 -0.0420 8.06 0.940 -0.0420 8.99 0.984 -0.0420 10.03 1.022 -0.0420 11.05 1.045 -0.0420 12.04 1.128 -0.0420 12.96 1.107 -0.0420 14.08 1.080 -0.0420 15.03 1.026 -0.0420 15.93 0.914 -0.0420 16.98 0.899 -0.0420 17.93 0.894 -0.0420 16.82 0.908 -0.0420 15.76 0.943 -0.0420 14.76 1.045 -0.0420 13.78 1.091 -0.0420 12.99 1.103 -0.0420 11.91 1.101 -0.0420 10.91 1.036 -0.0420 9.91 1.011 -0.0420 8.89 0.973 -0.0420 7.88 0.925 -0.0420 6.85 0.878 -0.0420 5.83 0.807 -0.0420 4.80 0.710 -0.0420 3.70 0.604 -0.0420 2.74 0.510 -0.0420 1.69 0.410 -0.0420 0.67 0.311 -0.0420 -0.42 0.143 -0.0420 -1.45 0.044 -0.0420 -2.54 -0.044 -0.0420 -3.59 -0.130 -0.0420 -4.51 -0.201 -0.0420 -5.62 -0.297 -0.0420 -6.62 -0.410 -0.0420 Tabulated from data in file CL00621.DAT & reduced using program Q02.00L File e374b.lft created on 09-12-1997 at 13:46:17 using program FORMAT :::::::::::::: E423.LFT :::::::::::::: Airfoil: E423 Builder: D. Glaze / M. Lazor Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60200 Number of angles of attack: 49 alpha / Cl / Cm -6.29 -0.023 -0.2460 -5.20 -0.146 -0.2460 -4.26 -0.257 -0.2460 -3.16 -0.307 -0.2460 -2.25 -0.238 -0.2460 -1.07 -0.007 -0.2460 -0.13 0.166 -0.2460 0.81 0.342 -0.2460 1.95 0.463 -0.2460 2.93 0.533 -0.2460 3.90 0.604 -0.2460 5.04 0.667 -0.2460 5.99 0.714 -0.2460 6.97 0.761 -0.2460 8.13 0.798 -0.2460 8.96 0.833 -0.2460 10.00 0.886 -0.2460 11.03 0.911 -0.2460 12.22 0.971 -0.2460 13.02 0.986 -0.2460 14.03 1.054 -0.2460 14.98 1.097 -0.2460 16.22 1.133 -0.2460 17.15 1.177 -0.2460 18.06 1.235 -0.2460 16.34 1.142 -0.2460 15.51 1.126 -0.2460 14.46 1.087 -0.2460 13.41 1.043 -0.2460 12.32 0.982 -0.2460 11.46 0.938 -0.2460 10.39 0.910 -0.2460 9.55 0.875 -0.2460 8.36 0.828 -0.2460 7.40 0.806 -0.2460 6.54 0.762 -0.2460 5.34 0.710 -0.2460 4.48 0.666 -0.2460 3.35 0.592 -0.2460 2.32 0.518 -0.2460 1.27 0.414 -0.2460 0.42 0.294 -0.2460 -0.63 0.062 -0.2460 -1.91 -0.142 -0.2460 -2.87 -0.259 -0.2460 -3.88 -0.275 -0.2460 -4.85 -0.170 -0.2460 -5.84 -0.070 -0.2460 -6.76 0.033 -0.2460 Tabulated from data in file AG00843.DAT & reduced using program Q02.00L Average Reynolds #: 100300 Number of angles of attack: 49 alpha / Cl / Cm -6.74 0.161 -0.2460 -4.91 0.199 -0.2460 -4.18 0.233 -0.2460 -3.15 0.324 -0.2460 -2.15 0.489 -0.2460 -1.09 0.719 -0.2460 -0.06 0.823 -0.2460 1.13 0.921 -0.2460 2.12 0.999 -0.2460 3.12 1.091 -0.2460 4.12 1.173 -0.2460 5.14 0.825 -0.2460 6.04 0.874 -0.2460 7.07 0.888 -0.2460 7.95 0.933 -0.2460 8.99 0.975 -0.2460 10.14 1.037 -0.2460 11.12 1.105 -0.2460 12.06 1.109 -0.2460 13.03 1.175 -0.2460 13.99 1.162 -0.2460 15.11 1.156 -0.2460 16.22 1.216 -0.2460 17.20 1.246 -0.2460 18.14 1.226 -0.2460 16.36 1.225 -0.2460 15.65 1.199 -0.2460 14.33 1.159 -0.2460 13.62 1.154 -0.2460 12.45 1.100 -0.2460 11.36 1.081 -0.2460 10.50 1.050 -0.2460 9.38 0.984 -0.2460 8.48 0.970 -0.2460 7.29 0.934 -0.2460 6.49 0.937 -0.2460 5.41 0.882 -0.2460 4.50 0.783 -0.2460 3.53 1.108 -0.2460 2.51 1.031 -0.2460 1.32 0.919 -0.2460 0.43 0.856 -0.2460 -0.74 0.747 -0.2460 -1.66 0.611 -0.2460 -2.85 0.367 -0.2460 -3.64 0.272 -0.2460 -4.78 0.190 -0.2460 -5.75 0.174 -0.2460 -6.82 0.162 -0.2460 Tabulated from data in file AG00845.DAT & reduced using program Q02.00L Average Reynolds #: 199400 Number of angles of attack: 49 alpha / Cl / Cm -6.28 0.178 -0.2460 -5.07 0.215 -0.2460 -4.08 0.285 -0.2460 -3.02 0.411 -0.2460 -2.17 0.690 -0.2460 -0.87 0.838 -0.2460 -0.08 0.915 -0.2460 1.04 1.023 -0.2460 1.97 1.109 -0.2460 3.16 1.220 -0.2460 4.10 1.306 -0.2460 5.08 1.382 -0.2460 6.33 1.491 -0.2460 7.07 1.546 -0.2460 8.17 1.633 -0.2460 9.31 1.722 -0.2460 10.30 1.796 -0.2460 11.23 1.864 -0.2460 12.37 1.940 -0.2460 13.36 1.991 -0.2460 14.39 2.048 -0.2460 15.43 2.058 -0.2460 16.31 2.050 -0.2460 17.30 2.023 -0.2460 18.36 1.976 -0.2460 16.48 2.045 -0.2460 15.87 2.053 -0.2460 14.59 2.055 -0.2460 13.82 2.019 -0.2460 12.66 1.956 -0.2460 11.50 1.880 -0.2460 10.65 1.819 -0.2460 9.59 1.733 -0.2460 8.48 1.649 -0.2460 7.67 1.589 -0.2460 6.42 1.488 -0.2460 5.61 1.420 -0.2460 4.50 1.324 -0.2460 3.44 1.234 -0.2460 2.43 1.143 -0.2460 1.41 1.047 -0.2460 0.41 0.950 -0.2460 -0.60 0.850 -0.2460 -1.60 0.748 -0.2460 -2.55 0.498 -0.2460 -3.78 0.312 -0.2460 -4.71 0.228 -0.2460 -5.71 0.173 -0.2460 -6.96 0.166 -0.2460 Tabulated from data in file CL00847.DAT & reduced using program Q02.00L Average Reynolds #: 299500 Number of angles of attack: 49 alpha / Cl / Cm -6.35 0.168 -0.2460 -5.18 0.222 -0.2460 -4.26 0.299 -0.2460 -3.30 0.418 -0.2460 -2.38 0.712 -0.2460 -1.35 0.820 -0.2460 -0.30 0.923 -0.2460 0.76 1.027 -0.2460 1.73 1.121 -0.2460 2.75 1.219 -0.2460 3.84 1.319 -0.2460 4.88 1.413 -0.2460 5.86 1.497 -0.2460 6.85 1.579 -0.2460 7.86 1.662 -0.2460 8.92 1.742 -0.2460 10.09 1.827 -0.2460 11.11 1.898 -0.2460 12.11 1.964 -0.2460 13.27 2.019 -0.2460 14.12 2.020 -0.2460 15.14 2.002 -0.2460 16.36 1.985 -0.2460 17.20 1.954 -0.2460 18.32 1.938 -0.2460 16.52 1.964 -0.2460 15.63 1.991 -0.2460 14.58 2.011 -0.2460 13.54 2.021 -0.2460 12.56 1.988 -0.2460 11.63 1.933 -0.2460 10.71 1.869 -0.2460 9.50 1.779 -0.2460 8.67 1.719 -0.2460 7.64 1.636 -0.2460 6.70 1.563 -0.2460 5.60 1.468 -0.2460 4.57 1.378 -0.2460 3.64 1.297 -0.2460 2.67 1.206 -0.2460 1.59 1.102 -0.2460 0.54 0.999 -0.2460 -0.34 0.912 -0.2460 -1.43 0.801 -0.2460 -2.36 0.702 -0.2460 -3.31 0.416 -0.2460 -4.60 0.256 -0.2460 -5.81 0.179 -0.2460 -6.83 0.160 -0.2460 Tabulated from data in file CL00849.DAT & reduced using program Q02.00L File e423.lft created on 09-12-1997 at 13:46:17 using program FORMAT :::::::::::::: LD79.LFT :::::::::::::: Airfoil: LD-79 Builder: L. DeWitt Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 59900 Number of angles of attack: 49 alpha / Cl / Cm -7.85 -0.509 -0.0900 -6.12 -0.441 -0.0900 -5.39 -0.373 -0.0900 -4.08 -0.193 -0.0900 -3.27 -0.079 -0.0900 -2.19 0.067 -0.0900 -1.11 0.206 -0.0900 -0.20 0.323 -0.0900 0.84 0.466 -0.0900 1.87 0.562 -0.0900 2.91 0.662 -0.0900 3.96 0.760 -0.0900 5.03 0.854 -0.0900 6.07 0.941 -0.0900 7.13 1.032 -0.0900 8.19 1.103 -0.0900 9.21 1.160 -0.0900 10.19 1.202 -0.0900 11.15 1.233 -0.0900 12.12 1.237 -0.0900 13.09 1.217 -0.0900 14.07 1.269 -0.0900 15.22 1.299 -0.0900 16.23 1.229 -0.0900 16.95 1.152 -0.0900 15.36 1.288 -0.0900 14.50 1.287 -0.0900 13.36 1.218 -0.0900 12.49 1.231 -0.0900 11.50 1.244 -0.0900 10.61 1.221 -0.0900 9.42 1.173 -0.0900 8.55 1.129 -0.0900 7.37 1.054 -0.0900 6.44 0.977 -0.0900 5.49 0.893 -0.0900 4.23 0.794 -0.0900 3.52 0.727 -0.0900 2.32 0.604 -0.0900 1.38 0.515 -0.0900 0.19 0.382 -0.0900 -0.75 0.237 -0.0900 -1.73 0.124 -0.0900 -2.96 -0.027 -0.0900 -3.91 -0.161 -0.0900 -4.91 -0.305 -0.0900 -5.76 -0.394 -0.0900 -6.94 -0.477 -0.0900 -8.08 -0.503 -0.0900 Tabulated from data in file FS00944.DAT & reduced using program Q02.00L Average Reynolds #: 100200 Number of angles of attack: 49 alpha / Cl / Cm -7.80 -0.520 -0.0900 -6.11 -0.441 -0.0900 -5.44 -0.380 -0.0900 -4.11 -0.173 -0.0900 -3.12 -0.026 -0.0900 -1.96 0.115 -0.0900 -1.19 0.214 -0.0900 -0.10 0.364 -0.0900 0.95 0.474 -0.0900 1.91 0.567 -0.0900 3.01 0.674 -0.0900 3.95 0.765 -0.0900 4.95 0.859 -0.0900 6.05 0.950 -0.0900 7.16 1.035 -0.0900 8.26 1.113 -0.0900 9.16 1.166 -0.0900 10.08 1.208 -0.0900 11.23 1.228 -0.0900 12.22 1.210 -0.0900 13.21 1.180 -0.0900 14.10 1.272 -0.0900 15.29 1.274 -0.0900 16.04 1.210 -0.0900 17.18 1.118 -0.0900 15.44 1.198 -0.0900 14.57 1.311 -0.0900 13.44 1.202 -0.0900 12.43 1.187 -0.0900 11.55 1.201 -0.0900 10.36 1.187 -0.0900 9.48 1.155 -0.0900 8.56 1.104 -0.0900 7.29 1.018 -0.0900 6.34 0.945 -0.0900 5.36 0.863 -0.0900 4.34 0.772 -0.0900 3.34 0.677 -0.0900 2.35 0.571 -0.0900 1.21 0.457 -0.0900 0.24 0.357 -0.0900 -0.65 0.250 -0.0900 -1.88 0.082 -0.0900 -2.77 -0.035 -0.0900 -3.75 -0.183 -0.0900 -5.11 -0.360 -0.0900 -6.02 -0.445 -0.0900 -6.88 -0.502 -0.0900 -7.98 -0.535 -0.0900 Tabulated from data in file FS00946.DAT & reduced using program Q02.00L Average Reynolds #: 150400 Number of angles of attack: 49 alpha / Cl / Cm -7.81 -0.516 -0.0900 -6.21 -0.435 -0.0900 -5.24 -0.341 -0.0900 -4.25 -0.184 -0.0900 -3.22 -0.030 -0.0900 -1.91 0.132 -0.0900 -1.22 0.231 -0.0900 -0.03 0.370 -0.0900 1.10 0.487 -0.0900 1.89 0.569 -0.0900 2.99 0.689 -0.0900 4.22 0.834 -0.0900 4.88 0.888 -0.0900 6.05 0.983 -0.0900 7.19 1.069 -0.0900 8.14 1.130 -0.0900 9.27 1.187 -0.0900 10.04 1.209 -0.0900 11.07 1.207 -0.0900 12.06 1.204 -0.0900 13.03 1.261 -0.0900 13.99 1.295 -0.0900 15.33 1.206 -0.0900 16.10 1.164 -0.0900 17.07 1.122 -0.0900 15.04 1.249 -0.0900 14.47 1.265 -0.0900 13.52 1.299 -0.0900 12.51 1.185 -0.0900 11.52 1.201 -0.0900 10.53 1.203 -0.0900 9.34 1.177 -0.0900 8.32 1.128 -0.0900 7.30 1.062 -0.0900 6.22 0.980 -0.0900 5.41 0.916 -0.0900 4.37 0.831 -0.0900 3.16 0.715 -0.0900 2.35 0.609 -0.0900 1.10 0.470 -0.0900 0.31 0.388 -0.0900 -0.72 0.274 -0.0900 -1.76 0.135 -0.0900 -2.96 -0.034 -0.0900 -4.14 -0.178 -0.0900 -4.85 -0.287 -0.0900 -5.87 -0.408 -0.0900 -6.94 -0.485 -0.0900 -7.93 -0.515 -0.0900 Tabulated from data in file FS00950.DAT & reduced using program Q02.00L Average Reynolds #: 200500 Number of angles of attack: 49 alpha / Cl / Cm -7.41 -0.523 -0.0900 -6.44 -0.484 -0.0900 -5.16 -0.347 -0.0900 -4.41 -0.228 -0.0900 -3.18 -0.031 -0.0900 -2.00 0.116 -0.0900 -1.20 0.221 -0.0900 -0.04 0.350 -0.0900 0.92 0.489 -0.0900 1.96 0.600 -0.0900 3.01 0.706 -0.0900 4.06 0.807 -0.0900 5.12 0.893 -0.0900 6.02 0.966 -0.0900 6.98 1.038 -0.0900 8.26 1.125 -0.0900 9.22 1.173 -0.0900 10.22 1.203 -0.0900 11.01 1.204 -0.0900 12.15 1.200 -0.0900 13.28 1.309 -0.0900 14.21 1.272 -0.0900 14.87 1.237 -0.0900 16.16 1.198 -0.0900 16.87 1.101 -0.0900 15.29 1.230 -0.0900 14.72 1.256 -0.0900 13.91 1.299 -0.0900 12.30 1.188 -0.0900 11.41 1.199 -0.0900 10.52 1.199 -0.0900 9.50 1.173 -0.0900 8.30 1.113 -0.0900 7.21 1.042 -0.0900 6.41 0.983 -0.0900 5.23 0.888 -0.0900 4.15 0.797 -0.0900 3.42 0.728 -0.0900 2.40 0.627 -0.0900 1.10 0.488 -0.0900 0.09 0.379 -0.0900 -0.94 0.229 -0.0900 -1.75 0.131 -0.0900 -3.08 -0.048 -0.0900 -3.84 -0.142 -0.0900 -4.90 -0.311 -0.0900 -5.98 -0.442 -0.0900 -6.77 -0.505 -0.0900 -7.83 -0.543 -0.0900 Tabulated from data in file FS00948.DAT & reduced using program Q02.00L File ld79.lft created on 09-12-1997 at 13:46:17 using program FORMAT :::::::::::::: M06GF1.LFT :::::::::::::: Airfoil: M06-13-128 (B) Builder: M. Allen Comment: gurney flap (h/c = 1.0%) Number of Reynolds #'s: 2 Average Reynolds #: 200400 Number of angles of attack: 51 alpha / Cl / Cm -5.11 -0.119 0.0040 -3.41 0.139 0.0040 -2.40 0.258 0.0040 -1.58 0.345 0.0040 -0.50 0.458 0.0040 0.46 0.462 0.0040 1.43 0.522 0.0040 2.62 0.603 0.0040 3.59 0.687 0.0040 4.60 0.796 0.0040 5.86 0.993 0.0040 6.57 1.105 0.0040 7.67 1.238 0.0040 8.86 1.375 0.0040 9.65 1.463 0.0040 10.67 1.568 0.0040 11.87 1.634 0.0040 12.82 1.592 0.0040 13.82 1.520 0.0040 14.70 1.474 0.0040 15.70 1.413 0.0040 16.86 1.368 0.0040 17.60 1.365 0.0040 18.72 1.364 0.0040 19.71 1.364 0.0040 20.65 1.371 0.0040 19.08 1.368 0.0040 18.22 1.349 0.0040 17.19 1.363 0.0040 16.22 1.383 0.0040 15.15 1.444 0.0040 14.24 1.497 0.0040 13.22 1.569 0.0040 12.08 1.627 0.0040 11.14 1.608 0.0040 9.99 1.493 0.0040 9.09 1.393 0.0040 7.98 1.266 0.0040 7.03 1.155 0.0040 5.94 0.998 0.0040 4.80 0.818 0.0040 4.03 0.732 0.0040 2.71 0.603 0.0040 1.99 0.547 0.0040 0.80 0.466 0.0040 -0.35 0.453 0.0040 -1.04 0.405 0.0040 -2.45 0.245 0.0040 -3.36 0.137 0.0040 -4.40 -0.002 0.0040 -5.33 -0.155 0.0040 Tabulated from data in file PG00914.DAT & reduced using program Q02.00L Average Reynolds #: 300400 Number of angles of attack: 51 alpha / Cl / Cm -5.13 -0.093 0.0040 -3.37 0.142 0.0040 -2.73 0.213 0.0040 -1.47 0.382 0.0040 -0.72 0.484 0.0040 0.41 0.516 0.0040 1.57 0.642 0.0040 2.49 0.742 0.0040 3.40 0.837 0.0040 4.60 0.966 0.0040 5.62 1.075 0.0040 6.66 1.186 0.0040 7.74 1.301 0.0040 8.67 1.403 0.0040 9.84 1.528 0.0040 10.82 1.618 0.0040 11.66 1.645 0.0040 12.71 1.588 0.0040 13.76 1.517 0.0040 14.70 1.477 0.0040 15.62 1.424 0.0040 16.69 1.399 0.0040 17.65 1.372 0.0040 18.58 1.391 0.0040 19.56 1.385 0.0040 20.58 1.389 0.0040 18.95 1.380 0.0040 18.00 1.385 0.0040 17.16 1.391 0.0040 16.18 1.404 0.0040 15.06 1.447 0.0040 14.24 1.490 0.0040 13.14 1.553 0.0040 12.28 1.611 0.0040 11.03 1.633 0.0040 10.20 1.562 0.0040 9.08 1.445 0.0040 8.21 1.350 0.0040 6.97 1.215 0.0040 5.99 1.109 0.0040 4.94 0.996 0.0040 3.86 0.882 0.0040 2.93 0.781 0.0040 1.92 0.671 0.0040 0.91 0.563 0.0040 -0.10 0.495 0.0040 -1.06 0.432 0.0040 -2.14 0.276 0.0040 -3.33 0.135 0.0040 -4.10 0.059 0.0040 -5.30 -0.131 0.0040 Tabulated from data in file PG00917.DAT & reduced using program Q02.00L File m06gf1.lft created on 09-12-1997 at 13:46:17 using program FORMAT :::::::::::::: M665.LFT :::::::::::::: Airfoil: M6 (65%) Builder: L. Spychalla Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60700 Number of angles of attack: 49 alpha / Cl / Cm -6.61 -0.507 -0.0270 -5.43 -0.426 -0.0270 -4.26 -0.344 -0.0270 -3.29 -0.270 -0.0270 -2.32 -0.193 -0.0270 -1.32 -0.045 -0.0270 -0.15 0.026 -0.0270 0.85 0.059 -0.0270 1.90 0.196 -0.0270 2.99 0.369 -0.0270 3.85 0.439 -0.0270 4.92 0.510 -0.0270 6.01 0.602 -0.0270 6.90 0.659 -0.0270 7.95 0.724 -0.0270 8.99 0.791 -0.0270 9.99 0.849 -0.0270 11.11 0.883 -0.0270 12.10 0.844 -0.0270 13.09 0.825 -0.0270 14.09 0.805 -0.0270 14.90 0.788 -0.0270 16.08 0.819 -0.0270 16.96 0.841 -0.0270 18.00 0.823 -0.0270 16.69 0.825 -0.0270 15.56 0.831 -0.0270 14.60 0.805 -0.0270 13.53 0.813 -0.0270 12.67 0.806 -0.0270 11.64 0.870 -0.0270 10.64 0.888 -0.0270 9.59 0.846 -0.0270 8.69 0.794 -0.0270 7.60 0.724 -0.0270 6.56 0.665 -0.0270 5.61 0.589 -0.0270 4.52 0.508 -0.0270 3.58 0.438 -0.0270 2.51 0.332 -0.0270 1.38 0.112 -0.0270 0.52 0.069 -0.0270 -0.66 0.027 -0.0270 -1.54 -0.094 -0.0270 -2.54 -0.182 -0.0270 -3.67 -0.274 -0.0270 -4.65 -0.349 -0.0270 -5.61 -0.418 -0.0270 -6.63 -0.494 -0.0270 Tabulated from data in file CF00757.DAT & reduced using program Q02.00L Average Reynolds #: 101000 Number of angles of attack: 49 alpha / Cl / Cm -6.70 -0.605 -0.0270 -5.28 -0.471 -0.0270 -4.35 -0.393 -0.0270 -3.29 -0.308 -0.0270 -2.23 -0.220 -0.0270 -1.18 -0.136 -0.0270 -0.10 0.021 -0.0270 0.76 0.075 -0.0270 1.85 0.264 -0.0270 2.95 0.370 -0.0270 4.04 0.455 -0.0270 5.01 0.533 -0.0270 6.11 0.619 -0.0270 6.97 0.679 -0.0270 8.05 0.756 -0.0270 9.11 0.827 -0.0270 10.14 0.883 -0.0270 11.13 0.888 -0.0270 11.93 0.896 -0.0270 13.11 0.876 -0.0270 14.03 0.834 -0.0270 14.95 0.826 -0.0270 16.00 0.830 -0.0270 17.08 0.815 -0.0270 17.99 0.852 -0.0270 16.58 0.825 -0.0270 15.62 0.822 -0.0270 14.69 0.862 -0.0270 13.56 0.840 -0.0270 12.65 0.836 -0.0270 11.67 0.900 -0.0270 10.59 0.889 -0.0270 9.54 0.842 -0.0270 8.68 0.788 -0.0270 7.55 0.709 -0.0270 6.64 0.646 -0.0270 5.50 0.559 -0.0270 4.58 0.486 -0.0270 3.46 0.398 -0.0270 2.53 0.322 -0.0270 1.44 0.185 -0.0270 0.50 0.023 -0.0270 -0.55 -0.010 -0.0270 -1.63 -0.175 -0.0270 -2.68 -0.261 -0.0270 -3.56 -0.333 -0.0270 -4.63 -0.417 -0.0270 -5.64 -0.506 -0.0270 -6.65 -0.594 -0.0270 Tabulated from data in file CF00759.DAT & reduced using program Q02.00L Average Reynolds #: 201700 Number of angles of attack: 49 alpha / Cl / Cm -6.50 -0.612 -0.0270 -5.40 -0.501 -0.0270 -4.38 -0.400 -0.0270 -3.19 -0.297 -0.0270 -2.15 -0.207 -0.0270 -1.26 -0.128 -0.0270 -0.29 -0.014 -0.0270 0.80 0.156 -0.0270 1.88 0.263 -0.0270 2.96 0.358 -0.0270 4.04 0.456 -0.0270 4.89 0.530 -0.0270 5.94 0.615 -0.0270 7.04 0.707 -0.0270 8.09 0.785 -0.0270 8.91 0.840 -0.0270 10.10 0.914 -0.0270 11.02 0.938 -0.0270 12.17 0.912 -0.0270 13.03 0.927 -0.0270 14.14 0.852 -0.0270 15.12 0.868 -0.0270 15.92 0.835 -0.0270 17.14 0.834 -0.0270 18.02 0.827 -0.0270 16.46 0.825 -0.0270 15.52 0.836 -0.0270 14.58 0.882 -0.0270 13.56 0.864 -0.0270 12.56 0.904 -0.0270 11.55 0.930 -0.0270 10.71 0.930 -0.0270 9.69 0.879 -0.0270 8.62 0.808 -0.0270 7.58 0.732 -0.0270 6.55 0.650 -0.0270 5.65 0.578 -0.0270 4.57 0.486 -0.0270 3.46 0.386 -0.0270 2.55 0.303 -0.0270 1.44 0.208 -0.0270 0.46 0.098 -0.0270 -0.67 -0.078 -0.0270 -1.68 -0.182 -0.0270 -2.59 -0.259 -0.0270 -3.74 -0.357 -0.0270 -4.64 -0.433 -0.0270 -5.66 -0.533 -0.0270 -6.59 -0.613 -0.0270 Tabulated from data in file CL00761.DAT & reduced using program Q02.00L Average Reynolds #: 302200 Number of angles of attack: 49 alpha / Cl / Cm -6.95 -0.654 -0.0270 -5.20 -0.491 -0.0270 -4.34 -0.408 -0.0270 -3.06 -0.295 -0.0270 -2.14 -0.213 -0.0270 -1.05 -0.090 -0.0270 -0.13 -0.002 -0.0270 0.82 0.129 -0.0270 1.95 0.260 -0.0270 2.95 0.371 -0.0270 3.86 0.455 -0.0270 4.90 0.547 -0.0270 6.05 0.636 -0.0270 6.88 0.704 -0.0270 7.89 0.784 -0.0270 9.00 0.864 -0.0270 9.98 0.927 -0.0270 10.95 0.966 -0.0270 12.02 0.961 -0.0270 12.94 0.956 -0.0270 14.01 0.904 -0.0270 14.97 0.845 -0.0270 16.05 0.862 -0.0270 17.01 0.865 -0.0270 18.04 0.860 -0.0270 16.42 0.858 -0.0270 15.59 0.839 -0.0270 14.46 0.869 -0.0270 13.66 0.910 -0.0270 12.40 0.957 -0.0270 11.58 0.964 -0.0270 10.79 0.960 -0.0270 9.64 0.905 -0.0270 8.73 0.841 -0.0270 7.63 0.760 -0.0270 6.61 0.678 -0.0270 5.53 0.592 -0.0270 4.58 0.514 -0.0270 3.49 0.417 -0.0270 2.41 0.313 -0.0270 1.39 0.201 -0.0270 0.36 0.056 -0.0270 -0.57 -0.041 -0.0270 -1.69 -0.172 -0.0270 -2.67 -0.265 -0.0270 -3.66 -0.351 -0.0270 -4.79 -0.451 -0.0270 -5.79 -0.547 -0.0270 -6.73 -0.632 -0.0270 Tabulated from data in file CL00763.DAT & reduced using program Q02.00L File m665.lft created on 09-12-1997 at 13:46:18 using program FORMAT :::::::::::::: M685.LFT :::::::::::::: Airfoil: M6 (85%) Builder: L. Spychalla Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60600 Number of angles of attack: 49 alpha / Cl / Cm -6.57 -0.480 -0.0690 -5.24 -0.387 -0.0690 -4.20 -0.325 -0.0690 -3.13 -0.256 -0.0690 -2.12 -0.195 -0.0690 -1.07 -0.048 -0.0690 -0.05 0.007 -0.0690 1.00 0.196 -0.0690 1.89 0.319 -0.0690 2.94 0.432 -0.0690 4.01 0.517 -0.0690 5.11 0.602 -0.0690 6.06 0.673 -0.0690 7.17 0.761 -0.0690 8.05 0.825 -0.0690 9.16 0.871 -0.0690 10.14 0.909 -0.0690 11.22 0.956 -0.0690 12.07 0.985 -0.0690 13.16 0.983 -0.0690 14.18 0.924 -0.0690 15.17 0.841 -0.0690 16.00 0.841 -0.0690 17.07 0.839 -0.0690 18.14 0.835 -0.0690 16.53 0.839 -0.0690 15.69 0.865 -0.0690 14.65 0.842 -0.0690 13.68 0.993 -0.0690 12.64 1.013 -0.0690 11.56 0.993 -0.0690 10.67 0.952 -0.0690 9.68 0.901 -0.0690 8.62 0.862 -0.0690 7.50 0.789 -0.0690 6.62 0.718 -0.0690 5.49 0.629 -0.0690 4.40 0.544 -0.0690 3.56 0.471 -0.0690 2.48 0.377 -0.0690 1.41 0.238 -0.0690 0.28 0.048 -0.0690 -0.55 -0.050 -0.0690 -1.69 -0.124 -0.0690 -2.70 -0.241 -0.0690 -3.74 -0.299 -0.0690 -4.81 -0.369 -0.0690 -5.74 -0.430 -0.0690 -6.68 -0.489 -0.0690 Tabulated from data in file CL00665.DAT & reduced using program Q02.00L Average Reynolds #: 100700 Number of angles of attack: 49 alpha / Cl / Cm -6.62 -0.511 -0.0690 -5.31 -0.411 -0.0690 -4.16 -0.340 -0.0690 -3.28 -0.291 -0.0690 -2.14 -0.206 -0.0690 -1.21 -0.046 -0.0690 0.04 0.181 -0.0690 0.99 0.297 -0.0690 1.95 0.383 -0.0690 2.95 0.457 -0.0690 3.94 0.531 -0.0690 5.13 0.627 -0.0690 6.14 0.711 -0.0690 7.15 0.794 -0.0690 8.18 0.860 -0.0690 9.17 0.903 -0.0690 10.13 0.950 -0.0690 11.06 0.993 -0.0690 12.18 1.020 -0.0690 13.21 0.985 -0.0690 14.10 0.907 -0.0690 15.00 0.847 -0.0690 16.18 0.828 -0.0690 17.03 0.807 -0.0690 17.97 0.791 -0.0690 16.62 0.828 -0.0690 15.66 0.833 -0.0690 14.55 0.870 -0.0690 13.64 0.946 -0.0690 12.66 1.019 -0.0690 11.69 1.013 -0.0690 10.67 0.975 -0.0690 9.60 0.922 -0.0690 8.73 0.878 -0.0690 7.65 0.824 -0.0690 6.51 0.732 -0.0690 5.55 0.654 -0.0690 4.62 0.577 -0.0690 3.63 0.498 -0.0690 2.47 0.409 -0.0690 1.56 0.330 -0.0690 0.45 0.219 -0.0690 -0.53 0.064 -0.0690 -1.62 -0.152 -0.0690 -2.70 -0.262 -0.0690 -3.63 -0.301 -0.0690 -4.58 -0.359 -0.0690 -5.68 -0.434 -0.0690 -6.76 -0.518 -0.0690 Tabulated from data in file CL00714.DAT & reduced using program Q02.00L Average Reynolds #: 201300 Number of angles of attack: 49 alpha / Cl / Cm -6.70 -0.546 -0.0690 -4.97 -0.408 -0.0690 -4.24 -0.361 -0.0690 -3.02 -0.233 -0.0690 -1.80 -0.075 -0.0690 -0.99 -0.008 -0.0690 0.23 0.163 -0.0690 1.06 0.269 -0.0690 2.27 0.381 -0.0690 3.10 0.455 -0.0690 4.27 0.564 -0.0690 5.11 0.638 -0.0690 6.22 0.748 -0.0690 7.39 0.833 -0.0690 8.19 0.871 -0.0690 9.34 0.931 -0.0690 10.12 0.971 -0.0690 11.17 1.012 -0.0690 12.19 1.031 -0.0690 13.15 1.034 -0.0690 14.14 0.965 -0.0690 15.26 0.857 -0.0690 16.47 0.827 -0.0690 17.21 0.837 -0.0690 18.44 0.819 -0.0690 16.46 0.830 -0.0690 15.39 0.862 -0.0690 14.47 0.922 -0.0690 13.56 1.019 -0.0690 12.41 1.027 -0.0690 11.61 1.015 -0.0690 10.40 0.974 -0.0690 9.51 0.930 -0.0690 8.33 0.866 -0.0690 7.42 0.822 -0.0690 6.48 0.757 -0.0690 5.21 0.634 -0.0690 4.22 0.546 -0.0690 3.56 0.489 -0.0690 2.23 0.366 -0.0690 1.22 0.276 -0.0690 0.18 0.146 -0.0690 -0.86 -0.007 -0.0690 -1.89 -0.094 -0.0690 -2.90 -0.215 -0.0690 -3.80 -0.338 -0.0690 -4.79 -0.400 -0.0690 -5.74 -0.469 -0.0690 -6.67 -0.541 -0.0690 Tabulated from data in file CL00722.DAT & reduced using program Q02.00L Average Reynolds #: 302100 Number of angles of attack: 49 alpha / Cl / Cm -6.46 -0.541 -0.0690 -5.10 -0.437 -0.0690 -4.24 -0.372 -0.0690 -3.02 -0.213 -0.0690 -2.14 -0.113 -0.0690 -0.94 -0.020 -0.0690 0.03 0.078 -0.0690 0.88 0.229 -0.0690 1.86 0.344 -0.0690 3.00 0.456 -0.0690 4.11 0.560 -0.0690 4.91 0.633 -0.0690 6.05 0.731 -0.0690 7.05 0.802 -0.0690 8.01 0.851 -0.0690 9.03 0.912 -0.0690 10.18 0.975 -0.0690 11.10 1.012 -0.0690 12.24 1.037 -0.0690 13.48 1.057 -0.0690 14.22 1.012 -0.0690 15.60 0.889 -0.0690 16.50 0.835 -0.0690 17.33 0.812 -0.0690 18.25 0.826 -0.0690 16.19 0.838 -0.0690 15.17 0.914 -0.0690 14.29 0.974 -0.0690 13.53 1.039 -0.0690 12.50 1.047 -0.0690 11.45 1.013 -0.0690 10.31 0.972 -0.0690 9.52 0.931 -0.0690 8.31 0.858 -0.0690 7.44 0.812 -0.0690 6.05 0.721 -0.0690 5.56 0.682 -0.0690 4.10 0.549 -0.0690 3.12 0.458 -0.0690 2.12 0.362 -0.0690 1.23 0.261 -0.0690 0.19 0.107 -0.0690 -0.83 -0.021 -0.0690 -1.86 -0.092 -0.0690 -2.90 -0.201 -0.0690 -3.89 -0.332 -0.0690 -4.91 -0.426 -0.0690 -5.90 -0.496 -0.0690 -6.91 -0.570 -0.0690 Tabulated from data in file CL00724.DAT & reduced using program Q02.00L File m685.lft created on 09-12-1997 at 13:46:18 using program FORMAT :::::::::::::: MA409GF4.LFT :::::::::::::: Airfoil: MA409 Builder: R. Cooney Comment: gurney flap (h/c = 0.4%) Number of Reynolds #'s: 4 Average Reynolds #: 60200 Number of angles of attack: 49 alpha / Cl / Cm -6.37 -0.373 -0.1150 -4.52 -0.241 -0.1150 -3.76 -0.187 -0.1150 -2.72 -0.106 -0.1150 -1.61 -0.014 -0.1150 -0.58 0.093 -0.1150 0.55 0.204 -0.1150 1.42 0.300 -0.1150 2.45 0.461 -0.1150 3.44 0.574 -0.1150 4.44 0.655 -0.1150 5.47 0.756 -0.1150 6.50 0.818 -0.1150 7.57 0.884 -0.1150 8.60 0.946 -0.1150 9.69 0.998 -0.1150 10.66 1.020 -0.1150 11.67 1.031 -0.1150 12.67 1.002 -0.1150 13.53 0.999 -0.1150 14.52 1.007 -0.1150 15.81 0.963 -0.1150 16.53 0.985 -0.1150 17.57 0.978 -0.1150 18.67 0.952 -0.1150 16.79 1.011 -0.1150 16.08 1.034 -0.1150 14.93 1.069 -0.1150 14.03 1.035 -0.1150 12.86 1.076 -0.1150 11.91 1.097 -0.1150 10.92 1.110 -0.1150 9.93 1.109 -0.1150 9.10 1.078 -0.1150 7.88 1.016 -0.1150 6.87 0.956 -0.1150 5.87 0.887 -0.1150 4.88 0.788 -0.1150 3.87 0.697 -0.1150 2.93 0.610 -0.1150 1.70 0.435 -0.1150 0.77 0.341 -0.1150 -0.12 0.249 -0.1150 -1.28 0.139 -0.1150 -2.36 0.049 -0.1150 -3.23 -0.024 -0.1150 -4.47 -0.122 -0.1150 -5.34 -0.203 -0.1150 -6.28 -0.317 -0.1150 Tabulated from data in file CL00920.DAT & reduced using program Q02.00L Average Reynolds #: 100400 Number of angles of attack: 49 alpha / Cl / Cm -5.81 -0.359 -0.1150 -4.80 -0.232 -0.1150 -3.73 -0.133 -0.1150 -2.66 -0.038 -0.1150 -1.66 0.063 -0.1150 -0.62 0.149 -0.1150 0.42 0.259 -0.1150 1.44 0.402 -0.1150 2.46 0.541 -0.1150 3.65 0.656 -0.1150 4.57 0.737 -0.1150 5.61 0.828 -0.1150 6.67 0.911 -0.1150 7.74 0.979 -0.1150 8.47 1.024 -0.1150 9.58 1.081 -0.1150 10.59 1.099 -0.1150 11.73 1.091 -0.1150 12.69 1.050 -0.1150 13.65 1.019 -0.1150 14.65 0.989 -0.1150 15.69 1.014 -0.1150 16.78 0.974 -0.1150 17.74 0.996 -0.1150 18.52 0.990 -0.1150 16.82 1.012 -0.1150 15.81 1.011 -0.1150 14.83 1.050 -0.1150 13.99 1.039 -0.1150 13.06 1.053 -0.1150 11.84 1.096 -0.1150 11.15 1.119 -0.1150 10.10 1.108 -0.1150 9.06 1.059 -0.1150 7.81 0.996 -0.1150 7.05 0.944 -0.1150 5.78 0.847 -0.1150 5.06 0.789 -0.1150 3.79 0.670 -0.1150 2.82 0.578 -0.1150 1.89 0.471 -0.1150 0.66 0.293 -0.1150 -0.29 0.198 -0.1150 -1.25 0.104 -0.1150 -2.19 0.026 -0.1150 -3.48 -0.093 -0.1150 -4.49 -0.184 -0.1150 -5.52 -0.281 -0.1150 -6.36 -0.412 -0.1150 Tabulated from data in file CL00922.DAT & reduced using program Q02.00L Average Reynolds #: 200600 Number of angles of attack: 49 alpha / Cl / Cm -6.10 -0.346 -0.1150 -4.48 -0.156 -0.1150 -3.71 -0.082 -0.1150 -2.46 0.039 -0.1150 -1.60 0.129 -0.1150 -0.53 0.243 -0.1150 0.61 0.354 -0.1150 1.46 0.447 -0.1150 2.46 0.551 -0.1150 3.53 0.656 -0.1150 4.48 0.751 -0.1150 5.57 0.850 -0.1150 6.66 0.940 -0.1150 7.73 1.015 -0.1150 8.77 1.079 -0.1150 9.70 1.130 -0.1150 10.63 1.158 -0.1150 11.74 1.151 -0.1150 12.57 1.155 -0.1150 13.66 1.102 -0.1150 14.52 1.082 -0.1150 15.49 1.074 -0.1150 16.80 1.047 -0.1150 17.65 1.044 -0.1150 18.66 1.009 -0.1150 16.81 1.021 -0.1150 15.89 1.065 -0.1150 15.10 1.077 -0.1150 13.87 1.111 -0.1150 13.13 1.146 -0.1150 11.79 1.154 -0.1150 10.98 1.168 -0.1150 9.73 1.127 -0.1150 9.11 1.093 -0.1150 7.80 1.021 -0.1150 7.10 0.974 -0.1150 5.76 0.864 -0.1150 5.08 0.802 -0.1150 3.69 0.665 -0.1150 3.02 0.599 -0.1150 1.62 0.460 -0.1150 0.92 0.384 -0.1150 -0.17 0.280 -0.1150 -1.21 0.166 -0.1150 -2.46 0.035 -0.1150 -3.36 -0.052 -0.1150 -4.18 -0.131 -0.1150 -5.27 -0.235 -0.1150 -6.28 -0.384 -0.1150 Tabulated from data in file CL00924.DAT & reduced using program Q02.00L Average Reynolds #: 300600 Number of angles of attack: 49 alpha / Cl / Cm -6.23 -0.330 -0.1150 -4.69 -0.153 -0.1150 -3.85 -0.069 -0.1150 -2.74 0.045 -0.1150 -1.59 0.169 -0.1150 -0.63 0.292 -0.1150 0.32 0.350 -0.1150 1.36 0.451 -0.1150 2.57 0.574 -0.1150 3.67 0.687 -0.1150 4.50 0.768 -0.1150 5.64 0.876 -0.1150 6.81 0.978 -0.1150 7.70 1.040 -0.1150 8.91 1.114 -0.1150 9.75 1.160 -0.1150 10.60 1.171 -0.1150 11.62 1.179 -0.1150 12.41 1.157 -0.1150 13.24 1.112 -0.1150 14.40 1.021 -0.1150 15.28 1.012 -0.1150 16.35 1.022 -0.1150 17.33 1.016 -0.1150 18.39 1.023 -0.1150 17.08 1.028 -0.1150 16.11 1.025 -0.1150 15.14 1.007 -0.1150 14.17 1.022 -0.1150 13.14 1.068 -0.1150 11.98 1.174 -0.1150 11.17 1.168 -0.1150 9.83 1.148 -0.1150 8.99 1.108 -0.1150 7.84 1.039 -0.1150 6.89 0.973 -0.1150 5.74 0.878 -0.1150 4.89 0.798 -0.1150 3.70 0.686 -0.1150 2.86 0.602 -0.1150 1.73 0.484 -0.1150 0.88 0.399 -0.1150 -0.35 0.320 -0.1150 -1.34 0.195 -0.1150 -2.21 0.102 -0.1150 -3.25 -0.008 -0.1150 -4.48 -0.131 -0.1150 -5.50 -0.233 -0.1150 -6.39 -0.358 -0.1150 Tabulated from data in file CL00926.DAT & reduced using program Q02.00L File ma409gf4.lft created on 09-12-1997 at 13:46:18 using program FORMAT :::::::::::::: MH32.LFT :::::::::::::: Airfoil: MH32 Builder: J. Tonnesen Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60100 Number of angles of attack: 49 alpha / Cl / Cm -5.85 -0.350 -0.0580 -4.55 -0.255 -0.0580 -3.51 -0.184 -0.0580 -2.60 -0.113 -0.0580 -1.58 -0.038 -0.0580 -0.52 0.069 -0.0580 0.49 0.154 -0.0580 1.50 0.320 -0.0580 2.49 0.473 -0.0580 3.68 0.625 -0.0580 4.56 0.705 -0.0580 5.63 0.793 -0.0580 6.73 0.883 -0.0580 7.62 0.952 -0.0580 8.72 1.020 -0.0580 9.79 1.081 -0.0580 10.84 1.124 -0.0580 11.86 1.153 -0.0580 12.78 1.038 -0.0580 13.77 0.957 -0.0580 14.66 0.957 -0.0580 15.68 0.947 -0.0580 16.73 0.945 -0.0580 17.74 0.972 -0.0580 18.80 0.967 -0.0580 17.41 0.969 -0.0580 16.33 0.953 -0.0580 15.29 0.957 -0.0580 14.27 0.956 -0.0580 13.33 0.998 -0.0580 12.36 1.137 -0.0580 11.29 1.132 -0.0580 10.30 1.092 -0.0580 9.31 1.040 -0.0580 8.29 0.978 -0.0580 7.23 0.907 -0.0580 6.21 0.823 -0.0580 5.35 0.746 -0.0580 4.23 0.653 -0.0580 3.20 0.547 -0.0580 2.15 0.399 -0.0580 1.27 0.244 -0.0580 0.14 0.101 -0.0580 -0.93 0.002 -0.0580 -1.96 -0.091 -0.0580 -2.98 -0.167 -0.0580 -3.88 -0.233 -0.0580 -4.95 -0.304 -0.0580 -5.91 -0.369 -0.0580 Tabulated from data in file JG00631.DAT & reduced using program Q02.00L Average Reynolds #: 100400 Number of angles of attack: 49 alpha / Cl / Cm -5.86 -0.372 -0.0580 -4.62 -0.276 -0.0580 -3.61 -0.202 -0.0580 -2.59 -0.116 -0.0580 -1.59 -0.027 -0.0580 -0.58 0.081 -0.0580 0.61 0.270 -0.0580 1.49 0.389 -0.0580 2.70 0.530 -0.0580 3.59 0.610 -0.0580 4.63 0.704 -0.0580 5.70 0.797 -0.0580 6.77 0.887 -0.0580 7.65 0.962 -0.0580 8.74 1.031 -0.0580 9.79 1.084 -0.0580 10.78 1.130 -0.0580 11.76 1.160 -0.0580 12.64 1.145 -0.0580 13.70 0.999 -0.0580 14.68 1.009 -0.0580 15.69 0.986 -0.0580 16.64 0.957 -0.0580 17.70 0.949 -0.0580 18.75 0.946 -0.0580 17.28 0.955 -0.0580 16.34 0.970 -0.0580 15.39 1.020 -0.0580 14.32 0.989 -0.0580 13.32 0.999 -0.0580 12.38 1.154 -0.0580 11.31 1.137 -0.0580 10.42 1.104 -0.0580 9.26 1.046 -0.0580 8.42 1.000 -0.0580 7.21 0.909 -0.0580 6.38 0.836 -0.0580 5.29 0.744 -0.0580 4.24 0.647 -0.0580 3.20 0.554 -0.0580 2.19 0.453 -0.0580 1.11 0.315 -0.0580 0.03 0.164 -0.0580 -0.97 0.013 -0.0580 -2.02 -0.080 -0.0580 -2.86 -0.158 -0.0580 -3.96 -0.244 -0.0580 -5.02 -0.316 -0.0580 -5.92 -0.391 -0.0580 Tabulated from data in file CL00633.DAT & reduced using program Q02.00L Average Reynolds #: 200700 Number of angles of attack: 49 alpha / Cl / Cm -5.95 -0.397 -0.0580 -4.54 -0.266 -0.0580 -3.51 -0.158 -0.0580 -2.61 -0.033 -0.0580 -1.45 0.102 -0.0580 -0.52 0.192 -0.0580 0.47 0.299 -0.0580 1.50 0.399 -0.0580 2.51 0.500 -0.0580 3.62 0.611 -0.0580 4.64 0.709 -0.0580 5.70 0.805 -0.0580 6.73 0.894 -0.0580 7.74 0.974 -0.0580 8.74 1.041 -0.0580 9.74 1.096 -0.0580 10.69 1.142 -0.0580 11.82 1.176 -0.0580 12.74 1.177 -0.0580 13.33 1.095 -0.0580 14.85 1.102 -0.0580 15.65 1.092 -0.0580 16.62 1.046 -0.0580 17.73 0.989 -0.0580 18.71 0.938 -0.0580 17.28 1.001 -0.0580 16.23 1.019 -0.0580 15.38 1.084 -0.0580 14.42 1.099 -0.0580 13.46 1.121 -0.0580 12.43 1.177 -0.0580 11.35 1.158 -0.0580 10.35 1.119 -0.0580 9.40 1.070 -0.0580 8.41 1.009 -0.0580 7.32 0.932 -0.0580 6.38 0.855 -0.0580 5.20 0.751 -0.0580 4.35 0.671 -0.0580 3.30 0.567 -0.0580 2.23 0.460 -0.0580 1.12 0.351 -0.0580 0.19 0.257 -0.0580 -0.79 0.157 -0.0580 -1.95 0.042 -0.0580 -2.96 -0.087 -0.0580 -3.96 -0.221 -0.0580 -4.98 -0.309 -0.0580 -5.98 -0.400 -0.0580 Tabulated from data in file CL00635.DAT & reduced using program Q02.00L Average Reynolds #: 301100 Number of angles of attack: 49 alpha / Cl / Cm -5.94 -0.389 -0.0580 -4.59 -0.217 -0.0580 -3.59 -0.104 -0.0580 -2.69 -0.008 -0.0580 -1.59 0.094 -0.0580 -0.54 0.187 -0.0580 0.57 0.305 -0.0580 1.54 0.405 -0.0580 2.60 0.517 -0.0580 3.66 0.624 -0.0580 4.70 0.724 -0.0580 5.69 0.815 -0.0580 6.64 0.899 -0.0580 7.85 0.995 -0.0580 8.76 1.060 -0.0580 9.74 1.120 -0.0580 10.83 1.173 -0.0580 11.68 1.199 -0.0580 12.77 1.207 -0.0580 13.72 1.205 -0.0580 14.32 1.151 -0.0580 15.56 1.112 -0.0580 16.56 1.088 -0.0580 17.53 0.994 -0.0580 18.53 0.960 -0.0580 17.42 1.007 -0.0580 16.38 1.083 -0.0580 15.38 1.122 -0.0580 14.49 1.161 -0.0580 13.50 1.180 -0.0580 12.38 1.203 -0.0580 11.38 1.186 -0.0580 10.30 1.143 -0.0580 9.34 1.089 -0.0580 8.33 1.022 -0.0580 7.29 0.944 -0.0580 6.35 0.865 -0.0580 5.33 0.773 -0.0580 4.22 0.664 -0.0580 3.25 0.571 -0.0580 2.24 0.469 -0.0580 1.06 0.347 -0.0580 0.19 0.257 -0.0580 -0.99 0.140 -0.0580 -2.02 0.053 -0.0580 -2.99 -0.043 -0.0580 -4.09 -0.163 -0.0580 -5.03 -0.269 -0.0580 -5.98 -0.391 -0.0580 Tabulated from data in file CL00637.DAT & reduced using program Q02.00L File mh32.lft created on 09-12-1997 at 13:46:18 using program FORMAT :::::::::::::: NACA2414.LFT :::::::::::::: Airfoil: NACA 2414 Builder: R. Bozzonetti Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60700 Number of angles of attack: 49 alpha / Cl / Cm -6.08 -0.498 -0.0590 -4.63 -0.415 -0.0590 -3.64 -0.356 -0.0590 -2.68 -0.282 -0.0590 -1.64 -0.200 -0.0590 -0.45 -0.054 -0.0590 0.54 0.112 -0.0590 1.64 0.283 -0.0590 2.58 0.392 -0.0590 3.50 0.490 -0.0590 4.63 0.590 -0.0590 5.58 0.670 -0.0590 6.73 0.758 -0.0590 7.67 0.836 -0.0590 8.82 0.925 -0.0590 9.74 0.979 -0.0590 10.84 1.034 -0.0590 11.70 1.074 -0.0590 12.75 1.111 -0.0590 13.80 1.140 -0.0590 14.71 0.745 -0.0590 15.67 0.766 -0.0590 16.71 0.769 -0.0590 17.78 0.783 -0.0590 18.68 0.803 -0.0590 17.01 0.755 -0.0590 16.05 0.713 -0.0590 15.11 0.746 -0.0590 14.13 0.748 -0.0590 13.11 0.749 -0.0590 12.40 1.102 -0.0590 11.18 1.044 -0.0590 10.27 1.004 -0.0590 9.30 0.950 -0.0590 8.06 0.861 -0.0590 7.07 0.786 -0.0590 6.32 0.730 -0.0590 5.01 0.627 -0.0590 4.25 0.559 -0.0590 2.98 0.440 -0.0590 1.99 0.343 -0.0590 0.97 0.186 -0.0590 -0.02 -0.006 -0.0590 -1.06 -0.141 -0.0590 -2.10 -0.228 -0.0590 -3.10 -0.310 -0.0590 -4.09 -0.375 -0.0590 -5.13 -0.433 -0.0590 -6.12 -0.487 -0.0590 Tabulated from data in file CL00773.DAT & reduced using program Q02.00L Average Reynolds #: 100900 Number of angles of attack: 49 alpha / Cl / Cm -6.06 -0.552 -0.0590 -4.62 -0.449 -0.0590 -3.63 -0.345 -0.0590 -2.41 -0.190 -0.0590 -1.38 -0.055 -0.0590 -0.42 0.089 -0.0590 0.56 0.228 -0.0590 1.66 0.393 -0.0590 2.62 0.462 -0.0590 4.10 0.578 -0.0590 4.55 0.616 -0.0590 5.74 0.715 -0.0590 6.73 0.792 -0.0590 7.69 0.870 -0.0590 8.86 0.974 -0.0590 9.76 1.039 -0.0590 10.87 1.077 -0.0590 11.71 1.108 -0.0590 12.78 1.146 -0.0590 13.82 1.169 -0.0590 14.82 1.167 -0.0590 15.75 0.780 -0.0590 16.79 0.764 -0.0590 17.64 0.757 -0.0590 18.71 0.816 -0.0590 17.00 0.768 -0.0590 16.12 0.794 -0.0590 15.10 0.791 -0.0590 14.08 0.804 -0.0590 13.20 1.166 -0.0590 12.16 1.122 -0.0590 11.20 1.085 -0.0590 10.24 1.053 -0.0590 9.24 0.996 -0.0590 8.21 0.908 -0.0590 7.16 0.817 -0.0590 6.10 0.734 -0.0590 5.03 0.646 -0.0590 4.22 0.580 -0.0590 3.16 0.494 -0.0590 2.08 0.411 -0.0590 1.03 0.338 -0.0590 -0.07 0.120 -0.0590 -0.89 0.005 -0.0590 -1.99 -0.138 -0.0590 -3.07 -0.273 -0.0590 -4.07 -0.385 -0.0590 -5.17 -0.487 -0.0590 -6.19 -0.550 -0.0590 Tabulated from data in file CL00775.DAT & reduced using program Q02.00L Average Reynolds #: 201800 Number of angles of attack: 49 alpha / Cl / Cm -6.23 -0.548 -0.0590 -4.52 -0.316 -0.0590 -3.40 -0.175 -0.0590 -2.42 -0.077 -0.0590 -1.37 0.019 -0.0590 -0.58 0.087 -0.0590 0.71 0.207 -0.0590 1.74 0.327 -0.0590 2.50 0.451 -0.0590 3.64 0.563 -0.0590 4.67 0.650 -0.0590 5.71 0.741 -0.0590 6.74 0.828 -0.0590 7.76 0.909 -0.0590 8.72 0.980 -0.0590 9.90 1.046 -0.0590 10.82 1.088 -0.0590 11.66 1.122 -0.0590 12.77 1.157 -0.0590 13.89 1.179 -0.0590 14.81 1.181 -0.0590 15.80 1.178 -0.0590 16.58 0.816 -0.0590 17.66 0.749 -0.0590 18.77 0.779 -0.0590 17.01 0.802 -0.0590 16.27 0.818 -0.0590 15.05 0.803 -0.0590 14.51 1.182 -0.0590 13.29 1.163 -0.0590 12.31 1.137 -0.0590 11.15 1.094 -0.0590 10.22 1.052 -0.0590 9.25 1.007 -0.0590 8.22 0.935 -0.0590 7.10 0.847 -0.0590 6.22 0.774 -0.0590 5.04 0.671 -0.0590 4.18 0.595 -0.0590 2.96 0.491 -0.0590 2.06 0.369 -0.0590 0.97 0.223 -0.0590 0.05 0.133 -0.0590 -1.11 0.030 -0.0590 -2.08 -0.054 -0.0590 -3.08 -0.147 -0.0590 -4.10 -0.262 -0.0590 -5.11 -0.399 -0.0590 -6.25 -0.551 -0.0590 Tabulated from data in file CL00777.DAT & reduced using program Q02.00L Average Reynolds #: 302500 Number of angles of attack: 49 alpha / Cl / Cm -6.17 -0.442 -0.0590 -4.52 -0.252 -0.0590 -3.68 -0.174 -0.0590 -2.54 -0.077 -0.0590 -1.60 0.006 -0.0590 -0.44 0.110 -0.0590 0.58 0.204 -0.0590 1.58 0.301 -0.0590 2.52 0.430 -0.0590 3.70 0.579 -0.0590 4.56 0.652 -0.0590 5.69 0.745 -0.0590 6.81 0.833 -0.0590 7.67 0.900 -0.0590 8.75 0.976 -0.0590 9.75 1.032 -0.0590 10.73 1.086 -0.0590 11.64 1.132 -0.0590 12.81 1.179 -0.0590 13.78 1.204 -0.0590 14.69 1.217 -0.0590 15.72 1.225 -0.0590 16.75 1.215 -0.0590 17.82 1.212 -0.0590 18.05 0.775 -0.0590 17.14 0.828 -0.0590 16.08 0.884 -0.0590 15.74 1.228 -0.0590 14.46 1.217 -0.0590 13.29 1.191 -0.0590 12.23 1.154 -0.0590 11.27 1.112 -0.0590 10.21 1.056 -0.0590 9.33 1.008 -0.0590 8.25 0.939 -0.0590 7.26 0.864 -0.0590 6.16 0.777 -0.0590 5.14 0.693 -0.0590 4.06 0.601 -0.0590 3.17 0.516 -0.0590 2.00 0.345 -0.0590 0.99 0.232 -0.0590 0.02 0.143 -0.0590 -1.02 0.047 -0.0590 -2.05 -0.045 -0.0590 -3.25 -0.149 -0.0590 -4.00 -0.215 -0.0590 -5.23 -0.342 -0.0590 -6.20 -0.456 -0.0590 Tabulated from data in file CL00779.DAT & reduced using program Q02.00L File naca2414.lft created on 09-12-1997 at 13:46:18 using program FORMAT :::::::::::::: NACA2415.LFT :::::::::::::: Airfoil: NACA 2415 Builder: D. Imes Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60700 Number of angles of attack: 49 alpha / Cl / Cm -6.05 -0.494 -0.0530 -4.64 -0.398 -0.0530 -3.46 -0.285 -0.0530 -2.56 -0.171 -0.0530 -1.63 -0.038 -0.0530 -0.42 0.073 -0.0530 0.64 0.141 -0.0530 1.45 0.221 -0.0530 2.65 0.337 -0.0530 3.48 0.418 -0.0530 4.74 0.547 -0.0530 5.58 0.642 -0.0530 6.71 0.789 -0.0530 7.73 0.880 -0.0530 8.71 0.953 -0.0530 9.77 1.006 -0.0530 10.72 1.043 -0.0530 11.87 1.099 -0.0530 12.80 1.129 -0.0530 13.70 1.149 -0.0530 14.69 0.702 -0.0530 15.57 0.712 -0.0530 16.60 0.724 -0.0530 17.77 0.745 -0.0530 18.70 0.842 -0.0530 17.07 0.726 -0.0530 16.11 0.721 -0.0530 15.15 0.726 -0.0530 14.18 0.696 -0.0530 13.24 0.733 -0.0530 12.24 0.735 -0.0530 11.25 1.073 -0.0530 10.19 1.029 -0.0530 9.17 0.984 -0.0530 8.27 0.936 -0.0530 7.14 0.845 -0.0530 6.27 0.766 -0.0530 5.22 0.638 -0.0530 4.20 0.503 -0.0530 2.99 0.334 -0.0530 2.16 0.276 -0.0530 0.93 0.181 -0.0530 0.01 0.135 -0.0530 -1.02 0.036 -0.0530 -1.99 -0.068 -0.0530 -3.15 -0.241 -0.0530 -4.04 -0.339 -0.0530 -5.21 -0.437 -0.0530 -6.05 -0.484 -0.0530 Tabulated from data in file CL00781.DAT & reduced using program Q02.00L Average Reynolds #: 101100 Number of angles of attack: 49 alpha / Cl / Cm -6.09 -0.518 -0.0530 -4.56 -0.298 -0.0530 -3.58 -0.162 -0.0530 -2.61 -0.051 -0.0530 -1.39 0.063 -0.0530 -0.45 0.141 -0.0530 0.49 0.274 -0.0530 1.75 0.468 -0.0530 2.58 0.520 -0.0530 3.70 0.613 -0.0530 4.66 0.698 -0.0530 5.65 0.784 -0.0530 6.68 0.867 -0.0530 7.85 0.957 -0.0530 8.89 1.025 -0.0530 9.72 1.063 -0.0530 10.71 1.103 -0.0530 11.79 1.148 -0.0530 12.78 1.176 -0.0530 13.65 1.188 -0.0530 14.49 0.767 -0.0530 15.65 0.730 -0.0530 16.60 0.711 -0.0530 17.57 0.784 -0.0530 18.70 0.823 -0.0530 17.15 0.740 -0.0530 16.13 0.747 -0.0530 15.08 0.737 -0.0530 14.08 0.769 -0.0530 13.12 0.821 -0.0530 12.38 1.173 -0.0530 11.28 1.125 -0.0530 10.31 1.081 -0.0530 9.33 1.034 -0.0530 8.32 0.985 -0.0530 7.26 0.904 -0.0530 6.14 0.812 -0.0530 5.12 0.724 -0.0530 4.02 0.627 -0.0530 3.17 0.555 -0.0530 2.13 0.479 -0.0530 1.07 0.378 -0.0530 -0.01 0.178 -0.0530 -1.06 0.087 -0.0530 -2.14 -0.012 -0.0530 -3.01 -0.099 -0.0530 -4.11 -0.239 -0.0530 -5.20 -0.394 -0.0530 -6.06 -0.494 -0.0530 Tabulated from data in file CL00783.DAT & reduced using program Q02.00L Average Reynolds #: 201700 Number of angles of attack: 49 alpha / Cl / Cm -6.04 -0.376 -0.0530 -4.31 -0.190 -0.0530 -3.58 -0.129 -0.0530 -2.52 -0.042 -0.0530 -1.46 0.053 -0.0530 -0.44 0.153 -0.0530 0.55 0.243 -0.0530 1.52 0.345 -0.0530 2.70 0.507 -0.0530 3.64 0.625 -0.0530 4.60 0.715 -0.0530 5.64 0.811 -0.0530 6.66 0.897 -0.0530 7.69 0.968 -0.0530 8.67 1.027 -0.0530 9.66 1.079 -0.0530 10.84 1.135 -0.0530 11.77 1.172 -0.0530 12.91 1.200 -0.0530 13.78 1.214 -0.0530 14.79 1.226 -0.0530 15.82 1.222 -0.0530 16.59 0.749 -0.0530 17.59 0.735 -0.0530 18.53 0.773 -0.0530 16.97 0.756 -0.0530 16.05 0.744 -0.0530 15.23 0.754 -0.0530 14.12 0.755 -0.0530 13.25 1.205 -0.0530 12.25 1.181 -0.0530 11.27 1.148 -0.0530 10.32 1.108 -0.0530 9.12 1.042 -0.0530 8.33 0.997 -0.0530 7.25 0.930 -0.0530 6.13 0.845 -0.0530 5.23 0.763 -0.0530 4.10 0.655 -0.0530 3.09 0.557 -0.0530 1.94 0.387 -0.0530 0.88 0.260 -0.0530 0.03 0.184 -0.0530 -1.14 0.076 -0.0530 -2.04 -0.007 -0.0530 -3.04 -0.091 -0.0530 -4.29 -0.194 -0.0530 -5.06 -0.260 -0.0530 -6.25 -0.401 -0.0530 Tabulated from data in file CL00785.DAT & reduced using program Q02.00L Average Reynolds #: 302500 Number of angles of attack: 49 alpha / Cl / Cm -6.11 -0.351 -0.0530 -4.52 -0.218 -0.0530 -3.57 -0.137 -0.0530 -2.66 -0.057 -0.0530 -1.47 0.057 -0.0530 -0.42 0.153 -0.0530 0.61 0.263 -0.0530 1.53 0.370 -0.0530 2.49 0.487 -0.0530 3.45 0.627 -0.0530 4.54 0.730 -0.0530 5.57 0.820 -0.0530 6.60 0.904 -0.0530 7.49 0.965 -0.0530 8.60 1.038 -0.0530 9.70 1.102 -0.0530 10.60 1.147 -0.0530 11.71 1.190 -0.0530 12.69 1.221 -0.0530 13.62 1.247 -0.0530 14.60 1.271 -0.0530 15.73 1.292 -0.0530 16.68 1.303 -0.0530 17.63 1.299 -0.0530 18.04 0.788 -0.0530 17.12 0.772 -0.0530 16.21 0.796 -0.0530 15.25 0.805 -0.0530 14.69 1.273 -0.0530 13.39 1.240 -0.0530 12.34 1.210 -0.0530 11.35 1.177 -0.0530 10.31 1.132 -0.0530 9.29 1.077 -0.0530 8.28 1.016 -0.0530 7.24 0.947 -0.0530 6.29 0.882 -0.0530 5.15 0.790 -0.0530 4.17 0.701 -0.0530 3.05 0.580 -0.0530 2.07 0.431 -0.0530 0.98 0.313 -0.0530 0.05 0.206 -0.0530 -1.01 0.097 -0.0530 -2.13 -0.011 -0.0530 -3.22 -0.113 -0.0530 -4.17 -0.197 -0.0530 -5.11 -0.276 -0.0530 -6.25 -0.375 -0.0530 Tabulated from data in file CL00787.DAT & reduced using program Q02.00L File naca2415.lft created on 09-12-1997 at 13:46:18 using program FORMAT :::::::::::::: RG15C.LFT :::::::::::::: Airfoil: RG15 (C) Builder: B. Champine / J. Robertson Comment: obechi surface: flap = 0 degs Number of Reynolds #'s: 4 Average Reynolds #: 60100 Number of angles of attack: 49 alpha / Cl / Cm -6.74 -0.410 -0.0580 -4.92 -0.272 -0.0580 -4.08 -0.219 -0.0580 -3.06 -0.147 -0.0580 -2.04 -0.076 -0.0580 -1.10 0.010 -0.0580 -0.14 0.101 -0.0580 1.09 0.273 -0.0580 2.07 0.433 -0.0580 3.07 0.537 -0.0580 4.06 0.599 -0.0580 5.06 0.685 -0.0580 6.09 0.765 -0.0580 7.07 0.832 -0.0580 8.10 0.900 -0.0580 9.07 0.939 -0.0580 10.28 0.985 -0.0580 11.20 0.999 -0.0580 12.11 0.974 -0.0580 13.08 0.961 -0.0580 14.11 0.927 -0.0580 15.12 0.968 -0.0580 16.13 1.004 -0.0580 17.11 1.061 -0.0580 18.36 1.107 -0.0580 16.62 1.052 -0.0580 15.41 0.995 -0.0580 14.59 0.976 -0.0580 13.63 0.922 -0.0580 12.49 0.980 -0.0580 11.51 0.974 -0.0580 10.68 0.989 -0.0580 9.52 0.945 -0.0580 8.59 0.908 -0.0580 7.52 0.851 -0.0580 6.47 0.779 -0.0580 5.41 0.700 -0.0580 4.56 0.630 -0.0580 3.35 0.558 -0.0580 2.36 0.489 -0.0580 1.33 0.328 -0.0580 0.33 0.173 -0.0580 -0.66 0.080 -0.0580 -1.66 -0.021 -0.0580 -2.77 -0.106 -0.0580 -3.70 -0.175 -0.0580 -4.88 -0.253 -0.0580 -5.71 -0.316 -0.0580 -6.86 -0.413 -0.0580 Tabulated from data in file AG00883.DAT & reduced using program Q02.00L Average Reynolds #: 100700 Number of angles of attack: 49 alpha / Cl / Cm -6.57 -0.426 -0.0580 -5.01 -0.262 -0.0580 -4.03 -0.185 -0.0580 -3.05 -0.112 -0.0580 -2.07 -0.049 -0.0580 -1.09 0.052 -0.0580 0.08 0.252 -0.0580 1.06 0.387 -0.0580 2.04 0.483 -0.0580 3.01 0.570 -0.0580 4.26 0.675 -0.0580 5.18 0.762 -0.0580 6.14 0.843 -0.0580 7.14 0.921 -0.0580 8.09 0.967 -0.0580 9.06 1.016 -0.0580 10.27 1.062 -0.0580 11.12 1.055 -0.0580 12.13 1.013 -0.0580 13.05 0.991 -0.0580 14.27 0.943 -0.0580 15.21 0.951 -0.0580 16.29 0.941 -0.0580 17.25 0.944 -0.0580 18.20 0.977 -0.0580 16.40 0.969 -0.0580 15.56 0.947 -0.0580 14.56 0.973 -0.0580 13.48 0.942 -0.0580 12.48 0.994 -0.0580 11.49 1.078 -0.0580 10.53 1.072 -0.0580 9.68 1.036 -0.0580 8.48 0.976 -0.0580 7.55 0.932 -0.0580 6.50 0.865 -0.0580 5.43 0.771 -0.0580 4.59 0.698 -0.0580 3.36 0.594 -0.0580 2.33 0.510 -0.0580 1.34 0.417 -0.0580 0.32 0.289 -0.0580 -0.69 0.117 -0.0580 -1.65 -0.013 -0.0580 -2.62 -0.084 -0.0580 -3.82 -0.179 -0.0580 -4.86 -0.260 -0.0580 -5.90 -0.343 -0.0580 -6.74 -0.409 -0.0580 Tabulated from data in file AG00885.DAT & reduced using program Q02.00L Average Reynolds #: 201000 Number of angles of attack: 49 alpha / Cl / Cm -6.42 -0.380 -0.0580 -5.11 -0.272 -0.0580 -4.04 -0.182 -0.0580 -2.94 -0.051 -0.0580 -1.91 0.065 -0.0580 -0.96 0.172 -0.0580 0.06 0.282 -0.0580 1.07 0.388 -0.0580 2.08 0.492 -0.0580 3.09 0.594 -0.0580 4.10 0.689 -0.0580 5.11 0.785 -0.0580 6.10 0.871 -0.0580 7.09 0.940 -0.0580 8.07 1.001 -0.0580 9.03 1.049 -0.0580 10.23 1.088 -0.0580 11.08 1.111 -0.0580 12.07 1.099 -0.0580 13.32 1.014 -0.0580 14.01 1.005 -0.0580 15.12 0.961 -0.0580 16.16 0.939 -0.0580 17.32 0.901 -0.0580 18.13 0.927 -0.0580 16.30 0.922 -0.0580 15.50 0.944 -0.0580 14.29 0.984 -0.0580 13.49 0.997 -0.0580 12.65 1.064 -0.0580 11.57 1.091 -0.0580 10.57 1.091 -0.0580 9.62 1.068 -0.0580 8.55 1.018 -0.0580 7.51 0.956 -0.0580 6.59 0.895 -0.0580 5.50 0.808 -0.0580 4.42 0.708 -0.0580 3.54 0.626 -0.0580 2.27 0.502 -0.0580 1.40 0.412 -0.0580 0.32 0.299 -0.0580 -0.66 0.195 -0.0580 -1.76 0.071 -0.0580 -2.79 -0.047 -0.0580 -3.69 -0.160 -0.0580 -4.74 -0.258 -0.0580 -5.86 -0.345 -0.0580 -6.83 -0.429 -0.0580 Tabulated from data in file AG00887.DAT & reduced using program Q02.00L Average Reynolds #: 301400 Number of angles of attack: 49 alpha / Cl / Cm -6.55 -0.393 -0.0580 -4.88 -0.246 -0.0580 -4.09 -0.154 -0.0580 -2.94 -0.022 -0.0580 -1.78 0.090 -0.0580 -0.87 0.172 -0.0580 0.02 0.275 -0.0580 0.98 0.376 -0.0580 2.06 0.487 -0.0580 3.12 0.596 -0.0580 4.07 0.687 -0.0580 5.10 0.783 -0.0580 6.15 0.874 -0.0580 7.16 0.948 -0.0580 8.13 1.010 -0.0580 9.08 1.059 -0.0580 10.26 1.098 -0.0580 11.03 1.125 -0.0580 12.09 1.118 -0.0580 12.88 1.083 -0.0580 14.34 0.999 -0.0580 15.26 0.939 -0.0580 16.18 0.905 -0.0580 16.99 0.903 -0.0580 18.07 0.942 -0.0580 16.33 0.891 -0.0580 15.39 0.924 -0.0580 14.44 0.962 -0.0580 13.62 1.033 -0.0580 12.49 1.092 -0.0580 11.67 1.114 -0.0580 10.63 1.107 -0.0580 9.69 1.077 -0.0580 8.61 1.032 -0.0580 7.62 0.973 -0.0580 6.57 0.899 -0.0580 5.48 0.810 -0.0580 4.36 0.708 -0.0580 3.45 0.620 -0.0580 2.30 0.504 -0.0580 1.39 0.409 -0.0580 0.26 0.291 -0.0580 -0.84 0.167 -0.0580 -1.82 0.076 -0.0580 -2.82 -0.022 -0.0580 -3.81 -0.133 -0.0580 -4.96 -0.266 -0.0580 -5.99 -0.352 -0.0580 -6.91 -0.433 -0.0580 Tabulated from data in file AG00889.DAT & reduced using program Q02.00L File rg15c.lft created on 09-12-1997 at 13:46:18 using program FORMAT :::::::::::::: RG15CF0.LFT :::::::::::::: Airfoil: RG15 (C) Builder: B. Champine / J. Robertson Comment: covering over obechi: flap = 0 degs Number of Reynolds #'s: 4 Average Reynolds #: 60500 Number of angles of attack: 49 alpha / Cl / Cm -6.72 -0.349 -0.0580 -5.11 -0.236 -0.0580 -4.23 -0.174 -0.0580 -3.08 -0.095 -0.0580 -2.22 -0.037 -0.0580 -1.10 0.068 -0.0580 0.04 0.181 -0.0580 0.90 0.272 -0.0580 2.07 0.488 -0.0580 2.94 0.592 -0.0580 4.10 0.691 -0.0580 4.99 0.762 -0.0580 6.19 0.853 -0.0580 7.09 0.917 -0.0580 7.99 0.971 -0.0580 9.20 1.020 -0.0580 10.20 1.060 -0.0580 11.05 1.065 -0.0580 12.17 1.056 -0.0580 13.02 1.004 -0.0580 14.14 0.968 -0.0580 15.00 0.967 -0.0580 16.26 0.967 -0.0580 16.95 0.978 -0.0580 18.17 0.932 -0.0580 16.56 0.983 -0.0580 15.59 0.992 -0.0580 14.63 0.992 -0.0580 13.68 0.971 -0.0580 12.56 1.055 -0.0580 11.64 1.077 -0.0580 10.71 1.074 -0.0580 9.60 1.046 -0.0580 8.62 1.004 -0.0580 7.65 0.959 -0.0580 6.67 0.899 -0.0580 5.46 0.812 -0.0580 4.65 0.747 -0.0580 3.49 0.655 -0.0580 2.51 0.566 -0.0580 1.57 0.413 -0.0580 0.43 0.238 -0.0580 -0.66 0.124 -0.0580 -1.61 0.028 -0.0580 -2.73 -0.068 -0.0580 -3.69 -0.124 -0.0580 -4.63 -0.188 -0.0580 -5.77 -0.269 -0.0580 -6.71 -0.338 -0.0580 Tabulated from data in file FS00928.DAT & reduced using program Q02.00L Average Reynolds #: 100400 Number of angles of attack: 49 alpha / Cl / Cm -6.69 -0.394 -0.0580 -5.12 -0.267 -0.0580 -4.18 -0.196 -0.0580 -3.24 -0.116 -0.0580 -2.03 -0.034 -0.0580 -1.12 0.064 -0.0580 -0.16 0.221 -0.0580 1.07 0.410 -0.0580 2.00 0.506 -0.0580 2.93 0.589 -0.0580 4.18 0.700 -0.0580 5.12 0.785 -0.0580 6.21 0.875 -0.0580 7.19 0.946 -0.0580 8.16 0.986 -0.0580 9.12 1.032 -0.0580 10.34 1.076 -0.0580 11.20 1.082 -0.0580 12.23 1.092 -0.0580 13.15 0.984 -0.0580 14.06 0.964 -0.0580 15.12 0.938 -0.0580 16.08 0.918 -0.0580 17.16 0.900 -0.0580 18.15 0.912 -0.0580 16.56 0.912 -0.0580 15.50 0.920 -0.0580 14.46 0.954 -0.0580 13.62 0.979 -0.0580 12.64 1.060 -0.0580 11.69 1.073 -0.0580 10.58 1.091 -0.0580 9.54 1.042 -0.0580 8.70 1.005 -0.0580 7.62 0.956 -0.0580 6.57 0.893 -0.0580 5.52 0.806 -0.0580 4.44 0.717 -0.0580 3.38 0.621 -0.0580 2.57 0.548 -0.0580 1.38 0.434 -0.0580 0.35 0.294 -0.0580 -0.57 0.131 -0.0580 -1.64 -0.002 -0.0580 -2.73 -0.087 -0.0580 -3.63 -0.152 -0.0580 -4.85 -0.247 -0.0580 -5.76 -0.311 -0.0580 -6.87 -0.395 -0.0580 Tabulated from data in file FS00930.DAT & reduced using program Q02.00L Average Reynolds #: 201100 Number of angles of attack: 49 alpha / Cl / Cm -6.66 -0.388 -0.0580 -5.10 -0.259 -0.0580 -4.08 -0.175 -0.0580 -3.16 -0.075 -0.0580 -2.16 0.049 -0.0580 -0.94 0.189 -0.0580 0.08 0.297 -0.0580 1.14 0.399 -0.0580 2.14 0.499 -0.0580 3.13 0.599 -0.0580 4.11 0.699 -0.0580 5.00 0.796 -0.0580 6.14 0.894 -0.0580 7.25 0.970 -0.0580 8.23 1.027 -0.0580 9.04 1.067 -0.0580 10.21 1.102 -0.0580 11.06 1.126 -0.0580 12.11 1.098 -0.0580 13.14 1.048 -0.0580 14.19 0.970 -0.0580 15.00 0.969 -0.0580 16.18 0.915 -0.0580 17.01 0.914 -0.0580 18.23 0.919 -0.0580 16.33 0.918 -0.0580 15.55 0.938 -0.0580 14.30 0.977 -0.0580 13.64 1.026 -0.0580 12.54 1.066 -0.0580 11.69 1.109 -0.0580 10.73 1.106 -0.0580 9.62 1.082 -0.0580 8.67 1.044 -0.0580 7.50 0.977 -0.0580 6.69 0.924 -0.0580 5.44 0.824 -0.0580 4.47 0.736 -0.0580 3.46 0.625 -0.0580 2.47 0.524 -0.0580 1.35 0.411 -0.0580 0.32 0.306 -0.0580 -0.73 0.207 -0.0580 -1.65 0.102 -0.0580 -2.78 -0.031 -0.0580 -3.67 -0.141 -0.0580 -4.78 -0.244 -0.0580 -5.80 -0.324 -0.0580 -6.96 -0.418 -0.0580 Tabulated from data in file FS00932.DAT & reduced using program Q02.00L Average Reynolds #: 301500 Number of angles of attack: 49 alpha / Cl / Cm -6.17 -0.342 -0.0580 -5.18 -0.254 -0.0580 -4.05 -0.128 -0.0580 -2.94 -0.003 -0.0580 -1.94 0.096 -0.0580 -1.00 0.167 -0.0580 0.02 0.275 -0.0580 1.19 0.429 -0.0580 1.91 0.506 -0.0580 2.96 0.617 -0.0580 4.22 0.740 -0.0580 5.19 0.827 -0.0580 6.04 0.897 -0.0580 7.04 0.972 -0.0580 8.30 1.049 -0.0580 9.18 1.089 -0.0580 10.33 1.124 -0.0580 11.12 1.145 -0.0580 12.30 1.127 -0.0580 12.65 1.115 -0.0580 14.02 1.013 -0.0580 15.22 0.974 -0.0580 15.99 0.934 -0.0580 17.11 0.924 -0.0580 18.13 0.959 -0.0580 16.29 0.930 -0.0580 15.46 0.947 -0.0580 14.51 0.992 -0.0580 13.55 1.046 -0.0580 12.60 1.122 -0.0580 11.30 1.139 -0.0580 10.91 1.148 -0.0580 9.59 1.099 -0.0580 8.64 1.061 -0.0580 7.59 1.003 -0.0580 6.57 0.933 -0.0580 5.47 0.845 -0.0580 4.34 0.745 -0.0580 3.50 0.665 -0.0580 2.25 0.538 -0.0580 1.33 0.438 -0.0580 0.43 0.338 -0.0580 -0.82 0.182 -0.0580 -1.79 0.108 -0.0580 -2.77 0.012 -0.0580 -3.83 -0.107 -0.0580 -4.87 -0.224 -0.0580 -5.81 -0.314 -0.0580 -7.07 -0.426 -0.0580 Tabulated from data in file FS00934.DAT & reduced using program Q02.00L File rg15cf0.lft created on 09-12-1997 at 13:46:18 using program FORMAT :::::::::::::: RG15CF10.LFT :::::::::::::: Airfoil: RG15 (C) Builder: B. Champine / J. Robertson Comment: covering over obechi: flap = 10 degs Number of Reynolds #'s: 4 Average Reynolds #: 60100 Number of angles of attack: 49 alpha / Cl / Cm -6.70 -0.096 -0.1300 -5.04 0.051 -0.1300 -4.09 0.104 -0.1300 -3.08 0.201 -0.1300 -2.11 0.305 -0.1300 -1.15 0.396 -0.1300 -0.16 0.479 -0.1300 1.15 0.648 -0.1300 1.96 0.815 -0.1300 2.99 0.967 -0.1300 4.26 1.064 -0.1300 5.19 1.092 -0.1300 6.15 1.132 -0.1300 7.15 1.162 -0.1300 8.16 1.202 -0.1300 9.16 1.231 -0.1300 10.10 1.240 -0.1300 11.06 1.186 -0.1300 12.08 1.154 -0.1300 13.26 1.083 -0.1300 14.15 1.107 -0.1300 15.08 1.120 -0.1300 16.02 1.109 -0.1300 17.27 1.111 -0.1300 18.04 1.129 -0.1300 16.56 1.133 -0.1300 15.53 1.140 -0.1300 14.48 1.145 -0.1300 13.43 1.146 -0.1300 12.62 1.136 -0.1300 11.59 1.139 -0.1300 10.64 1.216 -0.1300 9.44 1.260 -0.1300 8.61 1.231 -0.1300 7.56 1.196 -0.1300 6.45 1.164 -0.1300 5.55 1.130 -0.1300 4.40 1.082 -0.1300 3.63 1.034 -0.1300 2.32 0.900 -0.1300 1.54 0.738 -0.1300 0.51 0.579 -0.1300 -0.76 0.429 -0.1300 -1.79 0.318 -0.1300 -2.81 0.221 -0.1300 -3.71 0.123 -0.1300 -4.86 0.047 -0.1300 -5.82 -0.023 -0.1300 -6.81 -0.124 -0.1300 Tabulated from data in file CL00964.DAT & reduced using program Q02.00L Average Reynolds #: 100000 Number of angles of attack: 49 alpha / Cl / Cm -6.74 -0.089 -0.1300 -5.08 0.100 -0.1300 -4.10 0.147 -0.1300 -3.12 0.213 -0.1300 -2.10 0.317 -0.1300 -1.12 0.431 -0.1300 -0.09 0.559 -0.1300 0.93 0.712 -0.1300 1.95 0.894 -0.1300 3.25 1.006 -0.1300 3.96 1.054 -0.1300 5.28 1.122 -0.1300 5.96 1.144 -0.1300 7.30 1.192 -0.1300 8.27 1.228 -0.1300 9.06 1.250 -0.1300 10.01 1.236 -0.1300 11.11 1.243 -0.1300 12.13 1.091 -0.1300 13.08 1.093 -0.1300 14.15 1.071 -0.1300 15.08 1.066 -0.1300 16.08 1.078 -0.1300 17.09 1.094 -0.1300 18.22 1.097 -0.1300 16.33 1.068 -0.1300 15.37 1.085 -0.1300 14.49 1.072 -0.1300 13.43 1.095 -0.1300 12.61 1.122 -0.1300 11.55 1.138 -0.1300 10.46 1.229 -0.1300 9.66 1.258 -0.1300 8.56 1.224 -0.1300 7.64 1.193 -0.1300 6.55 1.148 -0.1300 5.46 1.112 -0.1300 4.60 1.074 -0.1300 3.48 1.002 -0.1300 2.41 0.935 -0.1300 1.32 0.779 -0.1300 0.46 0.621 -0.1300 -0.61 0.489 -0.1300 -1.64 0.364 -0.1300 -2.66 0.254 -0.1300 -3.72 0.157 -0.1300 -4.77 0.119 -0.1300 -5.87 -0.000 -0.1300 -6.90 -0.078 -0.1300 Tabulated from data in file CL00966.DAT & reduced using program Q02.00L Average Reynolds #: 200100 Number of angles of attack: 49 alpha / Cl / Cm -6.57 0.064 -0.1300 -5.08 0.193 -0.1300 -3.87 0.292 -0.1300 -2.97 0.365 -0.1300 -2.14 0.447 -0.1300 -1.04 0.546 -0.1300 0.05 0.731 -0.1300 1.00 0.855 -0.1300 2.09 0.947 -0.1300 3.13 1.022 -0.1300 4.22 1.089 -0.1300 5.00 1.125 -0.1300 6.25 1.179 -0.1300 7.16 1.220 -0.1300 8.28 1.260 -0.1300 9.13 1.280 -0.1300 10.09 1.289 -0.1300 10.99 1.273 -0.1300 12.11 1.178 -0.1300 13.05 1.151 -0.1300 14.32 1.108 -0.1300 15.10 1.084 -0.1300 16.12 1.100 -0.1300 17.29 1.109 -0.1300 18.11 1.097 -0.1300 16.26 1.069 -0.1300 15.42 1.082 -0.1300 14.45 1.103 -0.1300 13.36 1.126 -0.1300 12.50 1.167 -0.1300 11.47 1.242 -0.1300 10.52 1.284 -0.1300 9.55 1.296 -0.1300 8.52 1.259 -0.1300 7.50 1.224 -0.1300 6.57 1.185 -0.1300 5.36 1.132 -0.1300 4.37 1.086 -0.1300 3.39 1.028 -0.1300 2.42 0.960 -0.1300 1.42 0.885 -0.1300 0.38 0.776 -0.1300 -0.64 0.608 -0.1300 -1.68 0.488 -0.1300 -2.71 0.387 -0.1300 -3.75 0.287 -0.1300 -4.91 0.196 -0.1300 -5.91 0.110 -0.1300 -6.69 0.050 -0.1300 Tabulated from data in file CL00968.DAT & reduced using program Q02.00L Average Reynolds #: 300100 Number of angles of attack: 49 alpha / Cl / Cm -6.75 0.095 -0.1300 -5.24 0.246 -0.1300 -4.19 0.311 -0.1300 -3.05 0.389 -0.1300 -2.11 0.519 -0.1300 -1.10 0.664 -0.1300 0.11 0.788 -0.1300 1.07 0.869 -0.1300 2.05 0.945 -0.1300 3.10 1.018 -0.1300 4.17 1.081 -0.1300 5.31 1.142 -0.1300 6.23 1.188 -0.1300 7.29 1.233 -0.1300 8.06 1.260 -0.1300 9.09 1.298 -0.1300 10.03 1.307 -0.1300 11.31 1.296 -0.1300 12.10 1.243 -0.1300 13.01 1.164 -0.1300 14.04 1.123 -0.1300 14.87 1.087 -0.1300 15.85 1.079 -0.1300 17.01 1.077 -0.1300 17.86 1.125 -0.1300 16.51 1.089 -0.1300 15.63 1.072 -0.1300 14.48 1.098 -0.1300 13.60 1.142 -0.1300 12.52 1.191 -0.1300 11.64 1.283 -0.1300 10.65 1.319 -0.1300 9.50 1.319 -0.1300 8.46 1.272 -0.1300 7.40 1.236 -0.1300 6.40 1.193 -0.1300 5.36 1.144 -0.1300 4.23 1.084 -0.1300 3.39 1.034 -0.1300 2.53 0.979 -0.1300 1.38 0.890 -0.1300 0.27 0.798 -0.1300 -0.80 0.691 -0.1300 -1.56 0.610 -0.1300 -2.85 0.399 -0.1300 -3.94 0.324 -0.1300 -4.79 0.284 -0.1300 -5.73 0.193 -0.1300 -6.66 0.100 -0.1300 Tabulated from data in file CL00962.DAT & reduced using program Q02.00L File rg15cf10.lft created on 09-12-1997 at 13:46:18 using program FORMAT :::::::::::::: RG15CF5.LFT :::::::::::::: Airfoil: RG15 (C) Builder: B. Champine / J. Robertson Comment: covering over obechi: flap = 5 degs Number of Reynolds #'s: 4 Average Reynolds #: 60400 Number of angles of attack: 49 alpha / Cl / Cm -6.66 -0.206 -0.1100 -5.05 -0.068 -0.1100 -4.08 -0.006 -0.1100 -3.11 0.054 -0.1100 -2.09 0.161 -0.1100 -1.08 0.266 -0.1100 -0.08 0.359 -0.1100 0.85 0.463 -0.1100 2.12 0.704 -0.1100 3.05 0.813 -0.1100 4.02 0.888 -0.1100 5.03 0.957 -0.1100 6.05 1.002 -0.1100 7.10 1.037 -0.1100 8.23 1.086 -0.1100 9.21 1.114 -0.1100 10.16 1.104 -0.1100 11.08 1.084 -0.1100 12.03 1.043 -0.1100 13.23 1.033 -0.1100 14.20 1.008 -0.1100 15.16 1.003 -0.1100 16.24 0.983 -0.1100 17.18 0.965 -0.1100 18.12 0.945 -0.1100 16.55 0.998 -0.1100 15.51 1.018 -0.1100 14.51 1.071 -0.1100 13.47 1.047 -0.1100 12.48 1.095 -0.1100 11.47 1.120 -0.1100 10.60 1.166 -0.1100 9.61 1.170 -0.1100 8.57 1.141 -0.1100 7.49 1.097 -0.1100 6.64 1.070 -0.1100 5.50 1.008 -0.1100 4.55 0.953 -0.1100 3.51 0.875 -0.1100 2.38 0.763 -0.1100 1.43 0.595 -0.1100 0.36 0.427 -0.1100 -0.63 0.335 -0.1100 -1.63 0.237 -0.1100 -2.62 0.131 -0.1100 -3.65 0.041 -0.1100 -4.70 -0.033 -0.1100 -5.68 -0.119 -0.1100 -6.65 -0.208 -0.1100 Tabulated from data in file CL00952.DAT & reduced using program Q02.00L Average Reynolds #: 100200 Number of angles of attack: 49 alpha / Cl / Cm -6.79 -0.258 -0.1100 -5.23 -0.120 -0.1100 -4.23 -0.027 -0.1100 -3.24 0.038 -0.1100 -2.22 0.137 -0.1100 -0.95 0.280 -0.1100 0.00 0.423 -0.1100 0.98 0.600 -0.1100 2.10 0.741 -0.1100 2.92 0.816 -0.1100 4.18 0.913 -0.1100 5.00 0.975 -0.1100 6.11 1.046 -0.1100 7.11 1.081 -0.1100 8.20 1.130 -0.1100 9.15 1.166 -0.1100 10.09 1.189 -0.1100 11.25 1.157 -0.1100 11.96 1.082 -0.1100 13.22 1.072 -0.1100 14.13 1.012 -0.1100 15.22 0.972 -0.1100 16.15 0.958 -0.1100 17.11 0.975 -0.1100 18.08 0.966 -0.1100 16.45 0.961 -0.1100 15.59 0.970 -0.1100 14.55 1.010 -0.1100 13.52 1.064 -0.1100 12.48 1.066 -0.1100 11.50 1.143 -0.1100 10.60 1.152 -0.1100 9.63 1.183 -0.1100 8.63 1.132 -0.1100 7.53 1.093 -0.1100 6.49 1.054 -0.1100 5.59 1.010 -0.1100 4.57 0.934 -0.1100 3.48 0.849 -0.1100 2.46 0.763 -0.1100 1.42 0.650 -0.1100 0.38 0.485 -0.1100 -0.63 0.313 -0.1100 -1.63 0.195 -0.1100 -2.80 0.071 -0.1100 -3.64 0.007 -0.1100 -4.75 -0.080 -0.1100 -5.85 -0.182 -0.1100 -6.76 -0.258 -0.1100 Tabulated from data in file CL00955.DAT & reduced using program Q02.00L Average Reynolds #: 200600 Number of angles of attack: 49 alpha / Cl / Cm -6.82 -0.128 -0.1100 -4.95 0.048 -0.1100 -4.11 0.115 -0.1100 -3.00 0.200 -0.1100 -1.93 0.304 -0.1100 -0.86 0.433 -0.1100 -0.13 0.525 -0.1100 0.97 0.649 -0.1100 2.06 0.751 -0.1100 3.12 0.848 -0.1100 4.18 0.936 -0.1100 5.22 1.012 -0.1100 6.10 1.064 -0.1100 7.20 1.120 -0.1100 8.07 1.157 -0.1100 9.21 1.194 -0.1100 10.19 1.225 -0.1100 11.02 1.212 -0.1100 12.00 1.190 -0.1100 13.24 1.115 -0.1100 14.09 1.060 -0.1100 15.25 1.004 -0.1100 16.24 0.980 -0.1100 17.09 0.987 -0.1100 18.08 1.010 -0.1100 16.28 0.983 -0.1100 15.34 0.985 -0.1100 14.61 1.021 -0.1100 13.35 1.075 -0.1100 12.52 1.120 -0.1100 11.62 1.190 -0.1100 10.64 1.218 -0.1100 9.43 1.195 -0.1100 8.69 1.174 -0.1100 7.53 1.129 -0.1100 6.61 1.083 -0.1100 5.43 1.016 -0.1100 4.49 0.952 -0.1100 3.31 0.855 -0.1100 2.36 0.771 -0.1100 1.39 0.678 -0.1100 0.46 0.581 -0.1100 -0.60 0.462 -0.1100 -1.83 0.304 -0.1100 -2.81 0.218 -0.1100 -3.70 0.134 -0.1100 -4.73 0.056 -0.1100 -5.74 -0.029 -0.1100 -6.76 -0.119 -0.1100 Tabulated from data in file CL00957.DAT & reduced using program Q02.00L Average Reynolds #: 300500 Number of angles of attack: 49 alpha / Cl / Cm -6.86 -0.131 -0.1100 -4.98 0.053 -0.1100 -4.16 0.135 -0.1100 -2.94 0.255 -0.1100 -1.88 0.365 -0.1100 -1.10 0.442 -0.1100 -0.04 0.543 -0.1100 1.12 0.657 -0.1100 2.06 0.748 -0.1100 3.10 0.846 -0.1100 4.16 0.933 -0.1100 5.22 1.012 -0.1100 6.18 1.072 -0.1100 7.20 1.124 -0.1100 8.24 1.170 -0.1100 9.25 1.203 -0.1100 10.22 1.240 -0.1100 11.03 1.230 -0.1100 12.22 1.196 -0.1100 13.11 1.147 -0.1100 14.13 1.059 -0.1100 15.09 1.005 -0.1100 16.12 0.990 -0.1100 17.08 1.066 -0.1100 17.92 1.087 -0.1100 16.31 1.011 -0.1100 15.56 0.995 -0.1100 14.35 1.050 -0.1100 13.47 1.130 -0.1100 12.54 1.208 -0.1100 11.35 1.240 -0.1100 10.64 1.236 -0.1100 9.38 1.197 -0.1100 8.63 1.178 -0.1100 7.41 1.132 -0.1100 6.41 1.082 -0.1100 5.38 1.024 -0.1100 4.35 0.948 -0.1100 3.32 0.866 -0.1100 2.24 0.767 -0.1100 1.17 0.650 -0.1100 0.40 0.566 -0.1100 -0.74 0.449 -0.1100 -1.60 0.361 -0.1100 -2.77 0.245 -0.1100 -3.79 0.152 -0.1100 -4.92 0.043 -0.1100 -5.76 -0.032 -0.1100 -6.99 -0.146 -0.1100 Tabulated from data in file CL00960.DAT & reduced using program Q02.00L File rg15cf5.lft created on 09-12-1997 at 13:46:18 using program FORMAT :::::::::::::: S1223.LFT :::::::::::::: Airfoil: S1223 Builder: Y. Tinel Comment: clean Number of Reynolds #'s: 2 Average Reynolds #: 149500 Number of angles of attack: 55 alpha / Cl / Cm -4.43 0.132 -0.2900 -3.39 0.344 -0.2900 -2.33 0.781 -0.2900 -1.25 0.913 -0.2900 -0.32 1.021 -0.2900 0.79 1.132 -0.2900 1.72 1.218 -0.2900 2.88 1.319 -0.2900 3.87 1.391 -0.2900 4.85 1.473 -0.2900 5.82 1.548 -0.2900 7.01 1.636 -0.2900 7.95 1.704 -0.2900 8.85 1.761 -0.2900 9.98 1.827 -0.2900 11.10 1.892 -0.2900 11.88 1.938 -0.2900 13.07 1.994 -0.2900 14.03 2.058 -0.2900 15.08 2.124 -0.2900 16.10 2.188 -0.2900 17.14 2.205 -0.2900 17.99 2.169 -0.2900 18.95 2.057 -0.2900 20.06 2.021 -0.2900 20.95 1.929 -0.2900 21.65 1.461 -0.2900 23.02 1.477 -0.2900 23.79 1.526 -0.2900 22.41 1.457 -0.2900 21.32 1.421 -0.2900 20.26 1.407 -0.2900 19.35 1.357 -0.2900 18.49 1.373 -0.2900 17.28 1.321 -0.2900 16.46 1.294 -0.2900 15.31 1.228 -0.2900 14.30 1.294 -0.2900 13.32 1.224 -0.2900 12.23 1.156 -0.2900 11.19 1.114 -0.2900 10.30 1.152 -0.2900 9.33 1.135 -0.2900 8.27 1.093 -0.2900 7.21 1.104 -0.2900 6.36 1.479 -0.2900 5.38 1.497 -0.2900 4.43 1.421 -0.2900 3.40 1.341 -0.2900 2.36 1.250 -0.2900 1.30 1.156 -0.2900 0.27 1.059 -0.2900 -0.79 0.940 -0.2900 -1.82 0.828 -0.2900 -2.91 0.464 -0.2900 Tabulated from data in file CL00697.DAT & reduced using program Q02.00L Average Reynolds #: 198900 Number of angles of attack: 59 alpha / Cl / Cm -5.53 0.077 -0.2900 -4.35 0.235 -0.2900 -3.45 0.341 -0.2900 -2.29 0.786 -0.2900 -1.20 0.911 -0.2900 -0.32 1.014 -0.2900 0.87 1.138 -0.2900 1.88 1.237 -0.2900 2.91 1.331 -0.2900 3.96 1.418 -0.2900 4.81 1.488 -0.2900 6.10 1.604 -0.2900 6.89 1.666 -0.2900 7.93 1.741 -0.2900 8.98 1.809 -0.2900 10.00 1.873 -0.2900 11.14 1.945 -0.2900 11.99 1.992 -0.2900 13.17 2.061 -0.2900 14.12 2.116 -0.2900 15.05 2.170 -0.2900 16.20 2.209 -0.2900 17.11 2.203 -0.2900 17.99 2.135 -0.2900 18.95 2.037 -0.2900 20.01 1.986 -0.2900 21.07 1.946 -0.2900 22.04 1.935 -0.2900 23.14 1.897 -0.2900 23.88 1.886 -0.2900 22.52 1.915 -0.2900 21.55 1.931 -0.2900 20.50 1.995 -0.2900 19.59 2.019 -0.2900 18.65 2.067 -0.2900 17.62 2.169 -0.2900 16.57 2.214 -0.2900 15.60 2.190 -0.2900 14.59 2.149 -0.2900 13.56 2.087 -0.2900 12.49 2.025 -0.2900 11.62 1.971 -0.2900 10.50 1.897 -0.2900 9.45 1.830 -0.2900 8.39 1.756 -0.2900 7.40 1.688 -0.2900 6.39 1.614 -0.2900 5.34 1.527 -0.2900 4.34 1.429 -0.2900 3.21 1.344 -0.2900 2.18 1.247 -0.2900 1.17 1.151 -0.2900 0.16 1.054 -0.2900 -0.84 0.939 -0.2900 -1.85 0.827 -0.2900 -2.74 0.542 -0.2900 -3.81 0.295 -0.2900 -4.94 0.167 -0.2900 -5.85 0.032 -0.2900 Tabulated from data in file CL00698.DAT & reduced using program Q02.00L File s1223.lft created on 09-12-1997 at 13:46:18 using program FORMAT :::::::::::::: S1223GF4.LFT :::::::::::::: Airfoil: S1223 Builder: Y. Tinel Comment: gurney flap (h/c = 0.4%) Number of Reynolds #'s: 1 Average Reynolds #: 198800 Number of angles of attack: 51 alpha / Cl / Cm -5.39 0.134 -0.2900 -4.32 0.276 -0.2900 -3.31 0.468 -0.2900 -2.35 0.929 -0.2900 -1.16 1.069 -0.2900 -0.23 1.179 -0.2900 1.04 1.304 -0.2900 1.80 1.377 -0.2900 2.87 1.477 -0.2900 3.95 1.543 -0.2900 5.10 1.630 -0.2900 5.97 1.699 -0.2900 7.17 1.787 -0.2900 8.17 1.858 -0.2900 9.13 1.921 -0.2900 9.98 1.970 -0.2900 11.26 2.046 -0.2900 12.15 2.097 -0.2900 13.21 2.152 -0.2900 14.09 2.198 -0.2900 15.12 2.235 -0.2900 16.11 2.253 -0.2900 17.08 2.213 -0.2900 18.09 2.130 -0.2900 18.94 2.043 -0.2900 20.12 2.025 -0.2900 18.36 2.117 -0.2900 17.64 2.161 -0.2900 16.58 2.252 -0.2900 15.59 2.257 -0.2900 14.60 2.226 -0.2900 13.59 2.182 -0.2900 12.57 2.122 -0.2900 11.51 2.064 -0.2900 10.45 1.994 -0.2900 9.56 1.938 -0.2900 8.43 1.866 -0.2900 7.23 1.780 -0.2900 6.30 1.713 -0.2900 5.41 1.644 -0.2900 4.17 1.545 -0.2900 3.33 1.497 -0.2900 2.19 1.402 -0.2900 1.05 1.291 -0.2900 0.23 1.214 -0.2900 -0.88 1.099 -0.2900 -1.91 0.970 -0.2900 -3.04 0.826 -0.2900 -3.91 0.324 -0.2900 -5.06 0.181 -0.2900 -5.91 0.032 -0.2900 Tabulated from data in file PG00912.DAT & reduced using program Q02.00L File s1223gf4.lft created on 09-12-1997 at 13:46:18 using program FORMAT :::::::::::::: S1223RTL.LFT :::::::::::::: Airfoil: S1223 RTL Builder: C. Richardson Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 100700 Number of angles of attack: 61 alpha / Cl / Cm -6.75 -0.464 -0.2480 -5.15 -0.285 -0.2480 -4.02 -0.041 -0.2480 -2.94 0.105 -0.2480 -1.91 0.458 -0.2480 -0.93 0.589 -0.2480 0.19 0.716 -0.2480 1.30 0.823 -0.2480 2.07 0.887 -0.2480 3.21 0.980 -0.2480 4.33 1.060 -0.2480 5.11 1.109 -0.2480 6.30 1.170 -0.2480 6.98 0.787 -0.2480 8.34 0.756 -0.2480 9.13 0.772 -0.2480 10.27 0.824 -0.2480 11.08 0.860 -0.2480 12.20 0.885 -0.2480 13.30 0.923 -0.2480 14.06 0.947 -0.2480 15.32 0.981 -0.2480 16.02 1.018 -0.2480 17.13 1.020 -0.2480 18.17 1.061 -0.2480 19.16 1.097 -0.2480 19.95 1.145 -0.2480 21.07 1.167 -0.2480 22.11 1.213 -0.2480 23.20 1.237 -0.2480 24.08 1.208 -0.2480 22.46 1.185 -0.2480 21.62 1.125 -0.2480 20.39 1.122 -0.2480 19.53 1.084 -0.2480 18.39 1.045 -0.2480 17.43 1.030 -0.2480 16.31 0.992 -0.2480 15.47 0.951 -0.2480 14.42 0.949 -0.2480 13.37 0.937 -0.2480 12.43 0.891 -0.2480 11.50 0.839 -0.2480 10.46 0.836 -0.2480 9.42 0.797 -0.2480 8.37 0.815 -0.2480 7.41 0.771 -0.2480 6.52 0.897 -0.2480 5.54 1.112 -0.2480 4.49 1.051 -0.2480 3.33 0.962 -0.2480 2.53 0.899 -0.2480 1.51 0.816 -0.2480 0.46 0.706 -0.2480 -0.71 0.577 -0.2480 -1.66 0.461 -0.2480 -2.78 0.154 -0.2480 -3.75 -0.053 -0.2480 -4.94 -0.249 -0.2480 -5.95 -0.394 -0.2480 -6.89 -0.447 -0.2480 Tabulated from data in file CL00970.DAT & reduced using program Q02.00L Average Reynolds #: 150100 Number of angles of attack: 61 alpha / Cl / Cm -6.03 0.031 -0.2480 -5.12 0.129 -0.2480 -3.97 0.247 -0.2480 -3.00 0.343 -0.2480 -2.14 0.731 -0.2480 -0.79 0.914 -0.2480 0.31 1.035 -0.2480 1.07 1.118 -0.2480 2.49 1.248 -0.2480 3.34 1.316 -0.2480 4.48 1.399 -0.2480 5.37 1.455 -0.2480 6.16 1.501 -0.2480 7.32 1.556 -0.2480 8.20 1.035 -0.2480 9.04 1.043 -0.2480 10.08 1.075 -0.2480 11.44 1.098 -0.2480 12.26 1.154 -0.2480 13.27 1.201 -0.2480 14.27 1.207 -0.2480 15.37 1.227 -0.2480 16.23 1.261 -0.2480 17.24 1.290 -0.2480 18.27 1.319 -0.2480 19.36 1.353 -0.2480 20.36 1.359 -0.2480 21.07 1.404 -0.2480 22.39 1.449 -0.2480 23.41 1.506 -0.2480 24.13 1.521 -0.2480 22.56 1.477 -0.2480 21.52 1.458 -0.2480 20.70 1.396 -0.2480 19.51 1.325 -0.2480 18.66 1.304 -0.2480 17.54 1.265 -0.2480 16.70 1.231 -0.2480 15.60 1.180 -0.2480 14.47 1.196 -0.2480 13.64 1.164 -0.2480 12.57 1.105 -0.2480 11.25 1.094 -0.2480 10.45 1.081 -0.2480 9.45 1.063 -0.2480 8.56 1.008 -0.2480 7.49 1.023 -0.2480 6.50 1.484 -0.2480 5.59 1.433 -0.2480 4.42 1.366 -0.2480 3.59 1.314 -0.2480 2.46 1.224 -0.2480 1.35 1.131 -0.2480 0.31 1.018 -0.2480 -0.50 0.927 -0.2480 -1.75 0.779 -0.2480 -2.61 0.478 -0.2480 -3.77 0.266 -0.2480 -4.72 0.170 -0.2480 -5.76 0.055 -0.2480 -6.71 -0.016 -0.2480 Tabulated from data in file CL00971.DAT & reduced using program Q02.00L Average Reynolds #: 200200 Number of angles of attack: 61 alpha / Cl / Cm -6.75 0.044 -0.2480 -4.98 0.163 -0.2480 -4.15 0.228 -0.2480 -3.05 0.355 -0.2480 -2.24 0.753 -0.2480 -0.90 0.929 -0.2480 0.24 1.058 -0.2480 1.15 1.153 -0.2480 2.32 1.252 -0.2480 3.23 1.327 -0.2480 4.18 1.399 -0.2480 5.21 1.465 -0.2480 6.42 1.547 -0.2480 7.44 1.621 -0.2480 8.44 1.679 -0.2480 9.36 1.721 -0.2480 10.31 1.765 -0.2480 11.26 1.804 -0.2480 12.09 1.134 -0.2480 13.08 1.156 -0.2480 14.09 1.183 -0.2480 15.06 1.217 -0.2480 16.04 1.244 -0.2480 17.27 1.263 -0.2480 18.13 1.302 -0.2480 19.10 1.310 -0.2480 20.28 1.402 -0.2480 21.20 1.453 -0.2480 22.16 1.474 -0.2480 23.23 1.535 -0.2480 23.99 1.549 -0.2480 22.74 1.479 -0.2480 21.66 1.440 -0.2480 20.68 1.388 -0.2480 19.44 1.330 -0.2480 18.57 1.272 -0.2480 17.55 1.283 -0.2480 16.65 1.233 -0.2480 15.65 1.235 -0.2480 14.48 1.173 -0.2480 13.51 1.155 -0.2480 12.64 1.154 -0.2480 11.47 1.123 -0.2480 10.50 1.091 -0.2480 9.60 1.095 -0.2480 8.42 1.064 -0.2480 7.67 1.059 -0.2480 6.73 1.551 -0.2480 5.49 1.473 -0.2480 4.70 1.428 -0.2480 3.60 1.342 -0.2480 2.51 1.253 -0.2480 1.56 1.172 -0.2480 0.55 1.077 -0.2480 -0.46 0.961 -0.2480 -1.46 0.844 -0.2480 -2.39 0.603 -0.2480 -3.70 0.259 -0.2480 -4.94 0.159 -0.2480 -5.73 0.145 -0.2480 -6.71 0.039 -0.2480 Tabulated from data in file CL00972.DAT & reduced using program Q02.00L Average Reynolds #: 250000 Number of angles of attack: 61 alpha / Cl / Cm -6.05 0.101 -0.2480 -5.05 0.176 -0.2480 -3.93 0.249 -0.2480 -3.09 0.369 -0.2480 -2.10 0.794 -0.2480 -0.99 0.930 -0.2480 -0.08 1.029 -0.2480 1.03 1.151 -0.2480 1.97 1.233 -0.2480 3.10 1.330 -0.2480 4.22 1.421 -0.2480 5.14 1.495 -0.2480 6.24 1.569 -0.2480 7.23 1.643 -0.2480 8.24 1.711 -0.2480 9.29 1.773 -0.2480 10.37 1.845 -0.2480 11.52 1.922 -0.2480 12.46 1.974 -0.2480 13.36 2.022 -0.2480 14.60 2.068 -0.2480 15.37 2.093 -0.2480 16.59 2.107 -0.2480 17.33 2.119 -0.2480 17.65 1.269 -0.2480 18.89 1.324 -0.2480 19.82 1.415 -0.2480 20.82 1.438 -0.2480 21.83 1.489 -0.2480 22.86 1.518 -0.2480 23.89 1.516 -0.2480 22.98 1.530 -0.2480 21.83 1.473 -0.2480 20.71 1.431 -0.2480 19.76 1.401 -0.2480 18.67 1.312 -0.2480 17.66 1.289 -0.2480 16.64 1.258 -0.2480 15.65 1.207 -0.2480 14.71 1.178 -0.2480 13.58 1.184 -0.2480 12.65 1.182 -0.2480 11.65 1.125 -0.2480 10.68 1.108 -0.2480 9.64 1.076 -0.2480 8.52 1.082 -0.2480 7.71 1.108 -0.2480 6.99 1.615 -0.2480 5.72 1.511 -0.2480 4.48 1.429 -0.2480 3.53 1.356 -0.2480 2.63 1.283 -0.2480 1.60 1.194 -0.2480 0.61 1.099 -0.2480 -0.36 0.989 -0.2480 -1.47 0.860 -0.2480 -2.53 0.651 -0.2480 -3.27 0.334 -0.2480 -4.63 0.179 -0.2480 -5.63 0.123 -0.2480 -6.71 0.064 -0.2480 Tabulated from data in file CL00973.DAT & reduced using program Q02.00L Average Reynolds #: 299700 Number of angles of attack: 61 alpha / Cl / Cm -5.94 0.131 -0.2480 -5.23 0.154 -0.2480 -4.06 0.255 -0.2480 -3.12 0.421 -0.2480 -2.33 0.773 -0.2480 -1.27 0.910 -0.2480 -0.25 1.023 -0.2480 0.80 1.141 -0.2480 1.84 1.239 -0.2480 2.85 1.327 -0.2480 3.89 1.417 -0.2480 4.97 1.507 -0.2480 6.02 1.583 -0.2480 7.01 1.659 -0.2480 8.20 1.738 -0.2480 9.10 1.803 -0.2480 10.26 1.878 -0.2480 11.31 1.966 -0.2480 12.26 2.022 -0.2480 13.30 2.069 -0.2480 14.37 2.112 -0.2480 15.48 2.148 -0.2480 16.49 2.174 -0.2480 17.44 2.185 -0.2480 18.44 2.207 -0.2480 19.40 2.230 -0.2480 20.43 2.225 -0.2480 18.29 1.311 -0.2480 22.12 1.519 -0.2480 22.91 1.551 -0.2480 23.94 1.555 -0.2480 22.95 1.544 -0.2480 21.94 1.493 -0.2480 20.96 1.473 -0.2480 19.97 1.403 -0.2480 18.95 1.388 -0.2480 17.90 1.318 -0.2480 16.93 1.272 -0.2480 15.88 1.226 -0.2480 14.92 1.215 -0.2480 13.95 1.169 -0.2480 12.90 1.158 -0.2480 11.87 1.150 -0.2480 10.83 1.126 -0.2480 9.89 1.102 -0.2480 8.90 1.118 -0.2480 7.91 1.281 -0.2480 6.79 1.641 -0.2480 5.78 1.560 -0.2480 4.66 1.475 -0.2480 3.65 1.389 -0.2480 2.72 1.310 -0.2480 1.67 1.216 -0.2480 0.79 1.132 -0.2480 -0.25 1.013 -0.2480 -1.38 0.884 -0.2480 -2.29 0.766 -0.2480 -3.36 0.356 -0.2480 -4.69 0.173 -0.2480 -5.61 0.152 -0.2480 -6.81 0.046 -0.2480 Tabulated from data in file CL00974.DAT & reduced using program Q02.00L File s1223rtl.lft created on 09-12-1997 at 13:46:18 using program FORMAT :::::::::::::: S4083A.LFT :::::::::::::: Airfoil: S4083 (A) Builder: M. Levoe Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60200 Number of angles of attack: 49 alpha / Cl / Cm -5.76 -0.320 -0.0990 -4.41 -0.157 -0.0990 -3.44 -0.065 -0.0990 -2.28 0.036 -0.0990 -1.30 0.120 -0.0990 -0.32 0.220 -0.0990 0.77 0.361 -0.0990 1.82 0.536 -0.0990 2.81 0.622 -0.0990 3.84 0.711 -0.0990 4.86 0.799 -0.0990 5.93 0.891 -0.0990 6.99 0.983 -0.0990 7.84 1.049 -0.0990 8.99 1.139 -0.0990 9.84 1.201 -0.0990 10.95 1.271 -0.0990 12.02 1.304 -0.0990 13.04 1.315 -0.0990 13.96 0.981 -0.0990 14.77 0.996 -0.0990 15.86 1.062 -0.0990 16.82 1.052 -0.0990 17.91 1.077 -0.0990 18.99 1.066 -0.0990 17.52 1.079 -0.0990 16.34 1.043 -0.0990 15.51 1.052 -0.0990 14.52 1.012 -0.0990 13.34 0.964 -0.0990 12.42 0.952 -0.0990 11.54 1.276 -0.0990 10.59 1.236 -0.0990 9.42 1.153 -0.0990 8.53 1.086 -0.0990 7.34 0.988 -0.0990 6.36 0.903 -0.0990 5.33 0.813 -0.0990 4.34 0.728 -0.0990 3.38 0.645 -0.0990 2.26 0.547 -0.0990 1.27 0.428 -0.0990 0.24 0.226 -0.0990 -0.92 0.113 -0.0990 -1.78 0.037 -0.0990 -2.96 -0.064 -0.0990 -3.96 -0.153 -0.0990 -4.94 -0.258 -0.0990 -5.98 -0.366 -0.0990 Tabulated from data in file CL00647.DAT & reduced using program Q02.00L Average Reynolds #: 100600 Number of angles of attack: 49 alpha / Cl / Cm -5.80 -0.334 -0.0990 -4.34 -0.129 -0.0990 -3.43 -0.045 -0.0990 -2.30 0.052 -0.0990 -1.24 0.143 -0.0990 -0.24 0.261 -0.0990 0.66 0.402 -0.0990 1.83 0.544 -0.0990 2.92 0.644 -0.0990 3.74 0.723 -0.0990 4.88 0.832 -0.0990 5.77 0.914 -0.0990 6.97 1.023 -0.0990 7.86 1.102 -0.0990 9.05 1.210 -0.0990 9.92 1.272 -0.0990 11.02 1.319 -0.0990 11.87 1.334 -0.0990 12.94 1.320 -0.0990 13.97 1.283 -0.0990 14.88 1.063 -0.0990 15.88 1.100 -0.0990 17.01 1.120 -0.0990 17.83 1.089 -0.0990 18.91 1.079 -0.0990 17.46 1.086 -0.0990 16.37 1.086 -0.0990 15.39 1.101 -0.0990 14.33 1.082 -0.0990 13.47 1.230 -0.0990 12.56 1.326 -0.0990 11.59 1.319 -0.0990 10.59 1.286 -0.0990 9.56 1.231 -0.0990 8.50 1.140 -0.0990 7.42 1.043 -0.0990 6.32 0.943 -0.0990 5.25 0.843 -0.0990 4.33 0.756 -0.0990 3.30 0.655 -0.0990 2.26 0.557 -0.0990 1.20 0.459 -0.0990 0.29 0.327 -0.0990 -0.80 0.156 -0.0990 -1.86 0.049 -0.0990 -3.00 -0.054 -0.0990 -3.89 -0.134 -0.0990 -5.27 -0.287 -0.0990 -5.92 -0.347 -0.0990 Tabulated from data in file CL00649.DAT & reduced using program Q02.00L Average Reynolds #: 200300 Number of angles of attack: 49 alpha / Cl / Cm -5.85 -0.352 -0.0990 -4.34 -0.148 -0.0990 -3.38 -0.047 -0.0990 -2.15 0.042 -0.0990 -1.42 0.143 -0.0990 -0.23 0.311 -0.0990 0.68 0.413 -0.0990 1.75 0.530 -0.0990 2.83 0.640 -0.0990 3.90 0.747 -0.0990 4.91 0.850 -0.0990 5.78 0.934 -0.0990 6.93 1.037 -0.0990 7.95 1.134 -0.0990 8.83 1.204 -0.0990 9.96 1.278 -0.0990 11.03 1.329 -0.0990 11.98 1.338 -0.0990 12.87 1.324 -0.0990 13.91 1.296 -0.0990 14.86 1.263 -0.0990 15.72 1.087 -0.0990 16.89 1.075 -0.0990 17.80 1.078 -0.0990 18.84 1.080 -0.0990 17.45 1.085 -0.0990 16.45 1.096 -0.0990 15.51 1.089 -0.0990 14.82 1.259 -0.0990 13.52 1.301 -0.0990 12.45 1.322 -0.0990 11.54 1.331 -0.0990 10.48 1.295 -0.0990 9.51 1.241 -0.0990 8.32 1.154 -0.0990 7.37 1.067 -0.0990 6.41 0.979 -0.0990 5.31 0.875 -0.0990 4.36 0.782 -0.0990 3.21 0.667 -0.0990 2.17 0.562 -0.0990 1.23 0.467 -0.0990 0.22 0.349 -0.0990 -0.76 0.231 -0.0990 -1.84 0.072 -0.0990 -2.96 -0.045 -0.0990 -3.87 -0.103 -0.0990 -4.83 -0.223 -0.0990 -5.98 -0.362 -0.0990 Tabulated from data in file CL00652.DAT & reduced using program Q02.00L Average Reynolds #: 300900 Number of angles of attack: 49 alpha / Cl / Cm -5.87 -0.349 -0.0990 -4.53 -0.166 -0.0990 -3.56 -0.055 -0.0990 -2.22 0.059 -0.0990 -1.48 0.169 -0.0990 -0.39 0.317 -0.0990 0.68 0.417 -0.0990 1.65 0.513 -0.0990 2.72 0.623 -0.0990 3.85 0.736 -0.0990 4.84 0.835 -0.0990 5.88 0.935 -0.0990 7.01 1.043 -0.0990 7.94 1.122 -0.0990 8.94 1.203 -0.0990 10.05 1.280 -0.0990 10.86 1.327 -0.0990 11.90 1.344 -0.0990 12.85 1.334 -0.0990 14.01 1.303 -0.0990 15.06 1.263 -0.0990 15.98 1.227 -0.0990 16.48 1.157 -0.0990 17.65 1.106 -0.0990 18.64 1.091 -0.0990 17.62 1.100 -0.0990 16.59 1.169 -0.0990 15.72 1.241 -0.0990 14.37 1.291 -0.0990 13.47 1.318 -0.0990 12.57 1.333 -0.0990 11.44 1.335 -0.0990 10.51 1.298 -0.0990 9.42 1.226 -0.0990 8.45 1.152 -0.0990 7.44 1.065 -0.0990 6.36 0.967 -0.0990 5.22 0.855 -0.0990 4.27 0.764 -0.0990 3.33 0.671 -0.0990 2.19 0.554 -0.0990 1.32 0.465 -0.0990 0.15 0.353 -0.0990 -0.90 0.250 -0.0990 -1.81 0.105 -0.0990 -3.29 -0.033 -0.0990 -3.94 -0.101 -0.0990 -4.90 -0.223 -0.0990 -5.92 -0.358 -0.0990 Tabulated from data in file CL00655.DAT & reduced using program Q02.00L File s4083a.lft created on 09-12-1997 at 13:46:18 using program FORMAT :::::::::::::: S4083B.LFT :::::::::::::: Airfoil: S4083 (B) Builder: J. Thomas Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60000 Number of angles of attack: 49 alpha / Cl / Cm -5.93 -0.314 -0.0990 -4.66 -0.175 -0.0990 -3.75 -0.083 -0.0990 -2.60 0.020 -0.0990 -1.66 0.108 -0.0990 -0.51 0.217 -0.0990 0.43 0.375 -0.0990 1.60 0.535 -0.0990 2.48 0.604 -0.0990 3.63 0.704 -0.0990 4.52 0.784 -0.0990 5.71 0.882 -0.0990 6.66 0.959 -0.0990 7.67 1.043 -0.0990 8.69 1.113 -0.0990 9.69 1.171 -0.0990 10.66 1.202 -0.0990 11.63 1.222 -0.0990 12.64 1.222 -0.0990 13.56 1.115 -0.0990 14.63 1.023 -0.0990 15.72 1.026 -0.0990 16.66 1.021 -0.0990 17.61 0.990 -0.0990 18.58 0.993 -0.0990 17.24 1.002 -0.0990 16.15 1.028 -0.0990 15.25 1.036 -0.0990 14.22 1.086 -0.0990 13.20 1.181 -0.0990 12.26 1.223 -0.0990 11.23 1.217 -0.0990 10.35 1.194 -0.0990 9.30 1.152 -0.0990 8.19 1.078 -0.0990 7.23 1.004 -0.0990 6.10 0.913 -0.0990 5.18 0.842 -0.0990 4.08 0.746 -0.0990 3.19 0.673 -0.0990 2.13 0.579 -0.0990 1.04 0.468 -0.0990 0.10 0.300 -0.0990 -1.03 0.165 -0.0990 -2.11 0.066 -0.0990 -3.01 -0.015 -0.0990 -4.14 -0.126 -0.0990 -5.11 -0.240 -0.0990 -6.08 -0.335 -0.0990 Tabulated from data in file CL00639.DAT & reduced using program Q02.00L Average Reynolds #: 100200 Number of angles of attack: 49 alpha / Cl / Cm -6.02 -0.352 -0.0990 -4.73 -0.197 -0.0990 -3.70 -0.074 -0.0990 -2.68 0.022 -0.0990 -1.62 0.124 -0.0990 -0.59 0.290 -0.0990 0.48 0.416 -0.0990 1.53 0.536 -0.0990 2.58 0.635 -0.0990 3.60 0.733 -0.0990 4.63 0.833 -0.0990 5.70 0.929 -0.0990 6.56 1.006 -0.0990 7.69 1.106 -0.0990 8.58 1.167 -0.0990 9.66 1.216 -0.0990 10.71 1.250 -0.0990 11.74 1.260 -0.0990 12.56 1.241 -0.0990 13.68 1.238 -0.0990 14.63 1.055 -0.0990 15.74 1.072 -0.0990 16.55 1.052 -0.0990 17.69 1.037 -0.0990 18.58 1.029 -0.0990 17.27 1.063 -0.0990 16.17 1.032 -0.0990 15.29 1.066 -0.0990 14.31 1.101 -0.0990 13.33 1.218 -0.0990 12.35 1.247 -0.0990 11.31 1.257 -0.0990 10.36 1.236 -0.0990 9.23 1.194 -0.0990 8.20 1.134 -0.0990 7.14 1.050 -0.0990 6.26 0.968 -0.0990 5.20 0.872 -0.0990 4.19 0.778 -0.0990 3.18 0.679 -0.0990 2.18 0.582 -0.0990 1.15 0.483 -0.0990 0.11 0.356 -0.0990 -0.92 0.217 -0.0990 -1.95 0.080 -0.0990 -3.13 -0.031 -0.0990 -4.18 -0.145 -0.0990 -5.20 -0.269 -0.0990 -6.21 -0.367 -0.0990 Tabulated from data in file CL00641.DAT & reduced using program Q02.00L Average Reynolds #: 200300 Number of angles of attack: 49 alpha / Cl / Cm -6.03 -0.368 -0.0990 -4.59 -0.178 -0.0990 -3.58 -0.046 -0.0990 -2.51 0.092 -0.0990 -1.53 0.219 -0.0990 -0.61 0.328 -0.0990 0.42 0.436 -0.0990 1.57 0.567 -0.0990 2.56 0.667 -0.0990 3.48 0.761 -0.0990 4.57 0.870 -0.0990 5.56 0.963 -0.0990 6.71 1.068 -0.0990 7.67 1.140 -0.0990 8.76 1.206 -0.0990 9.66 1.245 -0.0990 10.65 1.267 -0.0990 11.72 1.258 -0.0990 12.71 1.250 -0.0990 13.54 1.226 -0.0990 14.54 1.126 -0.0990 15.54 1.085 -0.0990 16.58 1.162 -0.0990 17.62 1.112 -0.0990 18.58 1.048 -0.0990 17.26 1.134 -0.0990 16.15 1.109 -0.0990 15.29 1.118 -0.0990 14.24 1.144 -0.0990 13.39 1.229 -0.0990 12.38 1.252 -0.0990 11.35 1.260 -0.0990 10.34 1.261 -0.0990 9.34 1.228 -0.0990 8.25 1.172 -0.0990 7.26 1.102 -0.0990 6.21 1.018 -0.0990 5.31 0.930 -0.0990 4.20 0.823 -0.0990 3.09 0.711 -0.0990 2.17 0.618 -0.0990 1.04 0.503 -0.0990 0.08 0.383 -0.0990 -1.00 0.277 -0.0990 -1.93 0.165 -0.0990 -3.10 -0.007 -0.0990 -4.12 -0.117 -0.0990 -5.01 -0.237 -0.0990 -6.12 -0.371 -0.0990 Tabulated from data in file CL00643.DAT & reduced using program Q02.00L Average Reynolds #: 300300 Number of angles of attack: 49 alpha / Cl / Cm -5.87 -0.349 -0.0990 -4.80 -0.201 -0.0990 -3.66 -0.027 -0.0990 -2.73 0.090 -0.0990 -1.73 0.243 -0.0990 -0.62 0.358 -0.0990 0.33 0.447 -0.0990 1.51 0.575 -0.0990 2.56 0.684 -0.0990 3.52 0.785 -0.0990 4.52 0.887 -0.0990 5.57 0.990 -0.0990 6.73 1.090 -0.0990 7.85 1.173 -0.0990 8.79 1.230 -0.0990 9.86 1.278 -0.0990 10.71 1.288 -0.0990 11.76 1.280 -0.0990 12.79 1.268 -0.0990 13.72 1.242 -0.0990 14.47 1.242 -0.0990 15.46 1.204 -0.0990 16.44 1.211 -0.0990 17.48 1.150 -0.0990 18.41 1.075 -0.0990 17.50 1.155 -0.0990 16.33 1.189 -0.0990 15.43 1.200 -0.0990 14.39 1.231 -0.0990 13.49 1.248 -0.0990 12.17 1.277 -0.0990 11.32 1.285 -0.0990 10.35 1.288 -0.0990 9.35 1.254 -0.0990 8.34 1.200 -0.0990 7.15 1.115 -0.0990 6.29 1.047 -0.0990 5.20 0.946 -0.0990 3.99 0.822 -0.0990 3.02 0.724 -0.0990 2.11 0.626 -0.0990 1.07 0.517 -0.0990 -0.12 0.401 -0.0990 -1.04 0.309 -0.0990 -1.97 0.209 -0.0990 -2.97 0.048 -0.0990 -4.09 -0.095 -0.0990 -5.16 -0.254 -0.0990 -5.97 -0.356 -0.0990 Tabulated from data in file CL00645.DAT & reduced using program Q02.00L File s4083b.lft created on 09-12-1997 at 13:46:18 using program FORMAT :::::::::::::: S5010.LFT :::::::::::::: Airfoil: S5010 Builder: O. Wilson Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60400 Number of angles of attack: 49 alpha / Cl / Cm -7.09 -0.552 -0.0070 -5.71 -0.401 -0.0070 -4.62 -0.298 -0.0070 -3.56 -0.200 -0.0070 -2.56 -0.131 -0.0070 -1.53 0.009 -0.0070 -0.50 0.126 -0.0070 0.52 0.221 -0.0070 1.54 0.310 -0.0070 2.58 0.397 -0.0070 3.62 0.484 -0.0070 4.65 0.569 -0.0070 5.72 0.657 -0.0070 6.54 0.728 -0.0070 7.63 0.823 -0.0070 8.73 0.916 -0.0070 9.55 0.981 -0.0070 10.61 1.058 -0.0070 11.64 1.104 -0.0070 12.64 1.133 -0.0070 13.59 0.893 -0.0070 14.64 0.875 -0.0070 15.71 0.874 -0.0070 16.53 0.910 -0.0070 17.69 0.913 -0.0070 16.13 0.909 -0.0070 15.16 0.885 -0.0070 14.23 0.879 -0.0070 13.14 0.949 -0.0070 12.21 0.962 -0.0070 11.36 1.088 -0.0070 10.12 1.017 -0.0070 9.18 0.942 -0.0070 8.09 0.851 -0.0070 7.13 0.766 -0.0070 6.21 0.683 -0.0070 5.08 0.586 -0.0070 4.18 0.514 -0.0070 3.10 0.423 -0.0070 2.03 0.334 -0.0070 0.95 0.243 -0.0070 -0.12 0.149 -0.0070 -1.00 0.057 -0.0070 -2.08 -0.096 -0.0070 -3.13 -0.181 -0.0070 -4.14 -0.267 -0.0070 -5.21 -0.368 -0.0070 -6.22 -0.467 -0.0070 -7.23 -0.564 -0.0070 Tabulated from data in file CL00765.DAT & reduced using program Q02.00L Average Reynolds #: 100800 Number of angles of attack: 49 alpha / Cl / Cm -7.25 -0.619 -0.0070 -5.57 -0.423 -0.0070 -4.66 -0.323 -0.0070 -3.70 -0.222 -0.0070 -2.70 -0.111 -0.0070 -1.60 -0.034 -0.0070 -0.52 0.071 -0.0070 0.54 0.163 -0.0070 1.59 0.259 -0.0070 2.63 0.354 -0.0070 3.43 0.429 -0.0070 4.56 0.535 -0.0070 5.68 0.639 -0.0070 6.53 0.720 -0.0070 7.70 0.829 -0.0070 8.63 0.911 -0.0070 9.78 1.007 -0.0070 10.61 1.058 -0.0070 11.66 1.098 -0.0070 12.71 1.121 -0.0070 13.66 0.903 -0.0070 14.63 0.881 -0.0070 15.72 0.878 -0.0070 16.56 0.885 -0.0070 17.69 0.892 -0.0070 16.18 0.892 -0.0070 15.18 0.873 -0.0070 14.22 0.922 -0.0070 13.33 1.121 -0.0070 12.19 1.109 -0.0070 11.27 1.078 -0.0070 10.33 1.030 -0.0070 9.25 0.947 -0.0070 8.27 0.858 -0.0070 7.07 0.746 -0.0070 6.00 0.649 -0.0070 5.12 0.572 -0.0070 4.17 0.486 -0.0070 3.07 0.383 -0.0070 1.98 0.282 -0.0070 0.89 0.184 -0.0070 0.00 0.105 -0.0070 -1.09 0.008 -0.0070 -2.17 -0.079 -0.0070 -3.05 -0.156 -0.0070 -4.11 -0.273 -0.0070 -5.18 -0.384 -0.0070 -6.27 -0.514 -0.0070 -7.24 -0.609 -0.0070 Tabulated from data in file AG00767.DAT & reduced using program Q02.00L Average Reynolds #: 201500 Number of angles of attack: 49 alpha / Cl / Cm -7.15 -0.628 -0.0070 -5.68 -0.455 -0.0070 -4.57 -0.345 -0.0070 -3.67 -0.261 -0.0070 -2.64 -0.169 -0.0070 -1.47 -0.060 -0.0070 -0.49 0.020 -0.0070 0.47 0.120 -0.0070 1.51 0.220 -0.0070 2.61 0.321 -0.0070 3.60 0.422 -0.0070 4.39 0.501 -0.0070 5.44 0.629 -0.0070 6.59 0.746 -0.0070 7.51 0.836 -0.0070 8.74 0.952 -0.0070 9.70 1.031 -0.0070 10.65 1.090 -0.0070 11.60 1.122 -0.0070 12.75 1.136 -0.0070 13.65 1.137 -0.0070 14.40 0.932 -0.0070 15.61 0.899 -0.0070 16.60 0.904 -0.0070 17.58 0.892 -0.0070 16.03 0.898 -0.0070 15.02 0.913 -0.0070 14.19 0.946 -0.0070 13.41 1.134 -0.0070 12.27 1.126 -0.0070 11.30 1.107 -0.0070 10.20 1.057 -0.0070 9.25 0.986 -0.0070 8.13 0.883 -0.0070 7.13 0.785 -0.0070 6.12 0.681 -0.0070 5.22 0.588 -0.0070 4.02 0.445 -0.0070 3.04 0.344 -0.0070 2.12 0.250 -0.0070 0.78 0.130 -0.0070 -0.05 0.048 -0.0070 -1.05 -0.053 -0.0070 -2.06 -0.136 -0.0070 -3.09 -0.231 -0.0070 -4.14 -0.324 -0.0070 -5.07 -0.408 -0.0070 -6.06 -0.517 -0.0070 -7.22 -0.646 -0.0070 Tabulated from data in file CL00769.DAT & reduced using program Q02.00L Average Reynolds #: 302300 Number of angles of attack: 49 alpha / Cl / Cm -7.17 -0.645 -0.0070 -5.62 -0.483 -0.0070 -4.67 -0.382 -0.0070 -3.65 -0.285 -0.0070 -2.54 -0.180 -0.0070 -1.55 -0.084 -0.0070 -0.56 -0.000 -0.0070 0.68 0.112 -0.0070 1.48 0.195 -0.0070 2.54 0.333 -0.0070 3.51 0.435 -0.0070 4.64 0.551 -0.0070 5.63 0.653 -0.0070 6.55 0.745 -0.0070 7.59 0.848 -0.0070 8.60 0.945 -0.0070 9.59 1.031 -0.0070 10.69 1.106 -0.0070 11.60 1.140 -0.0070 12.64 1.154 -0.0070 13.72 1.164 -0.0070 14.62 1.160 -0.0070 15.12 0.984 -0.0070 16.58 0.967 -0.0070 17.51 0.944 -0.0070 16.08 0.951 -0.0070 15.21 0.974 -0.0070 14.67 1.165 -0.0070 13.32 1.162 -0.0070 12.25 1.151 -0.0070 11.23 1.129 -0.0070 10.28 1.079 -0.0070 9.17 0.991 -0.0070 8.22 0.903 -0.0070 7.17 0.800 -0.0070 6.07 0.690 -0.0070 5.11 0.593 -0.0070 3.96 0.476 -0.0070 3.04 0.381 -0.0070 2.16 0.286 -0.0070 1.02 0.140 -0.0070 -0.07 0.041 -0.0070 -1.02 -0.043 -0.0070 -2.07 -0.141 -0.0070 -3.07 -0.238 -0.0070 -4.20 -0.343 -0.0070 -5.22 -0.446 -0.0070 -6.13 -0.547 -0.0070 -7.18 -0.651 -0.0070 Tabulated from data in file CL00771.DAT & reduced using program Q02.00L File s5010.lft created on 09-12-1997 at 13:46:18 using program FORMAT :::::::::::::: S7012B.LFT :::::::::::::: Airfoil: S7012 (B) Builder: M. Lachowski Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60700 Number of angles of attack: 49 alpha / Cl / Cm -6.02 -0.374 -0.0400 -4.67 -0.266 -0.0400 -3.49 -0.171 -0.0400 -2.51 -0.095 -0.0400 -1.55 -0.024 -0.0400 -0.43 0.078 -0.0400 0.52 0.182 -0.0400 1.54 0.384 -0.0400 2.70 0.523 -0.0400 3.73 0.615 -0.0400 4.57 0.689 -0.0400 5.82 0.796 -0.0400 6.70 0.872 -0.0400 7.74 0.955 -0.0400 8.78 1.027 -0.0400 9.78 1.073 -0.0400 10.76 1.105 -0.0400 11.71 1.122 -0.0400 12.78 1.073 -0.0400 13.68 1.037 -0.0400 14.79 0.983 -0.0400 15.79 1.031 -0.0400 16.76 1.005 -0.0400 17.80 0.995 -0.0400 18.64 1.014 -0.0400 17.28 1.044 -0.0400 16.29 1.010 -0.0400 15.35 1.027 -0.0400 14.41 1.051 -0.0400 13.31 1.066 -0.0400 12.45 1.126 -0.0400 11.41 1.137 -0.0400 10.33 1.102 -0.0400 9.25 1.049 -0.0400 8.34 1.001 -0.0400 7.36 0.934 -0.0400 6.38 0.853 -0.0400 5.22 0.748 -0.0400 4.29 0.664 -0.0400 3.32 0.576 -0.0400 2.18 0.463 -0.0400 1.24 0.313 -0.0400 0.16 0.143 -0.0400 -0.92 0.021 -0.0400 -1.98 -0.053 -0.0400 -2.88 -0.129 -0.0400 -4.01 -0.208 -0.0400 -4.97 -0.286 -0.0400 -6.05 -0.384 -0.0400 Tabulated from data in file CL00824.DAT & reduced using program Q02.00L Average Reynolds #: 100600 Number of angles of attack: 49 alpha / Cl / Cm -6.05 -0.424 -0.0400 -4.39 -0.258 -0.0400 -3.43 -0.176 -0.0400 -2.50 -0.098 -0.0400 -1.50 -0.020 -0.0400 -0.38 0.110 -0.0400 0.53 0.259 -0.0400 1.63 0.385 -0.0400 2.77 0.493 -0.0400 3.59 0.569 -0.0400 4.71 0.675 -0.0400 5.64 0.760 -0.0400 6.65 0.850 -0.0400 7.67 0.939 -0.0400 8.66 0.995 -0.0400 9.88 1.054 -0.0400 10.73 1.080 -0.0400 11.76 1.065 -0.0400 12.80 1.019 -0.0400 13.92 0.970 -0.0400 14.73 0.971 -0.0400 15.91 0.957 -0.0400 16.88 0.957 -0.0400 17.83 0.928 -0.0400 18.69 0.964 -0.0400 17.22 0.956 -0.0400 16.36 0.957 -0.0400 15.35 0.976 -0.0400 14.36 0.969 -0.0400 13.41 0.980 -0.0400 12.25 1.045 -0.0400 11.30 1.087 -0.0400 10.28 1.063 -0.0400 9.25 1.018 -0.0400 8.19 0.960 -0.0400 7.39 0.908 -0.0400 6.25 0.795 -0.0400 5.16 0.687 -0.0400 4.29 0.601 -0.0400 3.19 0.498 -0.0400 2.11 0.398 -0.0400 1.00 0.290 -0.0400 0.16 0.181 -0.0400 -0.98 -0.010 -0.0400 -2.06 -0.081 -0.0400 -2.93 -0.149 -0.0400 -4.07 -0.248 -0.0400 -4.99 -0.323 -0.0400 -6.19 -0.427 -0.0400 Tabulated from data in file CL00837.DAT & reduced using program Q02.00L Average Reynolds #: 201000 Number of angles of attack: 49 alpha / Cl / Cm -6.09 -0.417 -0.0400 -4.33 -0.251 -0.0400 -3.39 -0.165 -0.0400 -2.38 -0.063 -0.0400 -1.36 0.049 -0.0400 -0.39 0.146 -0.0400 0.73 0.262 -0.0400 1.72 0.362 -0.0400 2.55 0.450 -0.0400 3.70 0.571 -0.0400 4.63 0.666 -0.0400 5.82 0.785 -0.0400 6.77 0.874 -0.0400 7.68 0.945 -0.0400 8.83 1.024 -0.0400 9.69 1.064 -0.0400 10.75 1.088 -0.0400 11.76 1.121 -0.0400 12.93 1.090 -0.0400 13.65 1.057 -0.0400 14.82 0.994 -0.0400 15.61 1.001 -0.0400 16.83 0.973 -0.0400 17.80 0.973 -0.0400 18.67 0.935 -0.0400 17.26 0.954 -0.0400 16.17 0.984 -0.0400 15.35 0.991 -0.0400 14.22 1.038 -0.0400 13.10 1.059 -0.0400 12.27 1.121 -0.0400 11.22 1.092 -0.0400 10.36 1.079 -0.0400 9.29 1.041 -0.0400 8.16 0.966 -0.0400 7.27 0.900 -0.0400 6.33 0.815 -0.0400 5.11 0.694 -0.0400 4.17 0.599 -0.0400 3.23 0.500 -0.0400 1.97 0.369 -0.0400 0.99 0.268 -0.0400 0.01 0.164 -0.0400 -1.00 0.070 -0.0400 -2.07 -0.042 -0.0400 -3.04 -0.139 -0.0400 -4.13 -0.243 -0.0400 -5.19 -0.342 -0.0400 -6.02 -0.414 -0.0400 Tabulated from data in file CF00839.DAT & reduced using program Q02.00L Average Reynolds #: 301400 Number of angles of attack: 49 alpha / Cl / Cm -5.61 -0.378 -0.0400 -4.56 -0.275 -0.0400 -3.39 -0.152 -0.0400 -2.55 -0.064 -0.0400 -1.19 0.068 -0.0400 -0.35 0.141 -0.0400 0.72 0.248 -0.0400 1.78 0.364 -0.0400 2.54 0.448 -0.0400 3.81 0.581 -0.0400 4.74 0.679 -0.0400 5.85 0.791 -0.0400 6.83 0.881 -0.0400 7.77 0.960 -0.0400 8.78 1.036 -0.0400 9.80 1.091 -0.0400 10.74 1.115 -0.0400 11.83 1.148 -0.0400 12.53 1.151 -0.0400 13.75 1.121 -0.0400 14.73 1.104 -0.0400 15.74 1.008 -0.0400 16.67 0.989 -0.0400 17.68 0.985 -0.0400 18.78 0.969 -0.0400 16.98 0.990 -0.0400 16.23 1.003 -0.0400 15.10 1.079 -0.0400 14.22 1.090 -0.0400 13.24 1.149 -0.0400 12.09 1.136 -0.0400 11.39 1.127 -0.0400 10.32 1.102 -0.0400 9.28 1.060 -0.0400 8.29 0.993 -0.0400 7.37 0.921 -0.0400 6.06 0.804 -0.0400 5.31 0.732 -0.0400 4.22 0.619 -0.0400 3.10 0.499 -0.0400 1.97 0.376 -0.0400 1.05 0.275 -0.0400 0.09 0.172 -0.0400 -1.06 0.070 -0.0400 -2.08 -0.022 -0.0400 -3.12 -0.132 -0.0400 -4.16 -0.237 -0.0400 -5.12 -0.332 -0.0400 -6.21 -0.431 -0.0400 Tabulated from data in file CF00841.DAT & reduced using program Q02.00L File s7012b.lft created on 09-12-1997 at 13:46:18 using program FORMAT :::::::::::::: S7012BF5.LFT :::::::::::::: Airfoil: S7012 (B) Builder: M. Lachowski Comment: clean: flap = 5 degs Number of Reynolds #'s: 4 Average Reynolds #: 60500 Number of angles of attack: 49 alpha / Cl / Cm -6.05 -0.267 -0.1000 -4.61 -0.125 -0.1000 -3.60 -0.032 -0.1000 -2.57 0.047 -0.1000 -1.54 0.135 -0.1000 -0.52 0.245 -0.1000 0.51 0.355 -0.1000 1.60 0.532 -0.1000 2.66 0.686 -0.1000 3.70 0.799 -0.1000 4.73 0.885 -0.1000 5.78 0.970 -0.1000 6.65 1.035 -0.1000 7.71 1.090 -0.1000 8.76 1.136 -0.1000 9.80 1.163 -0.1000 10.78 1.131 -0.1000 11.76 1.125 -0.1000 12.72 1.096 -0.1000 13.67 1.025 -0.1000 14.66 1.040 -0.1000 15.75 1.040 -0.1000 16.79 1.005 -0.1000 17.62 0.980 -0.1000 18.64 0.997 -0.1000 17.17 1.219 -0.1000 16.33 1.192 -0.1000 15.25 1.146 -0.1000 14.21 1.117 -0.1000 13.22 1.095 -0.1000 12.23 1.035 -0.1000 11.30 1.136 -0.1000 10.15 1.144 -0.1000 9.37 1.126 -0.1000 8.34 1.098 -0.1000 7.35 1.046 -0.1000 6.29 0.986 -0.1000 5.16 0.895 -0.1000 4.09 0.808 -0.1000 3.26 0.733 -0.1000 2.22 0.608 -0.1000 1.17 0.430 -0.1000 0.14 0.276 -0.1000 -1.02 0.152 -0.1000 -2.03 0.048 -0.1000 -3.02 -0.030 -0.1000 -4.01 -0.111 -0.1000 -5.05 -0.206 -0.1000 -6.08 -0.297 -0.1000 Tabulated from data in file CL00855.DAT & reduced using program Q02.00L Average Reynolds #: 100300 Number of angles of attack: 49 alpha / Cl / Cm -6.03 -0.225 -0.1000 -4.57 -0.084 -0.1000 -3.47 0.002 -0.1000 -2.63 0.049 -0.1000 -1.38 0.167 -0.1000 -0.54 0.256 -0.1000 0.59 0.460 -0.1000 1.58 0.594 -0.1000 2.68 0.714 -0.1000 3.63 0.798 -0.1000 4.72 0.896 -0.1000 5.83 0.999 -0.1000 6.70 1.061 -0.1000 7.82 1.109 -0.1000 8.65 1.143 -0.1000 9.78 1.175 -0.1000 10.72 1.195 -0.1000 11.77 1.157 -0.1000 12.83 1.133 -0.1000 13.64 1.048 -0.1000 14.87 1.045 -0.1000 15.75 1.064 -0.1000 16.86 1.017 -0.1000 17.64 1.018 -0.1000 18.86 1.036 -0.1000 17.04 1.036 -0.1000 16.21 1.048 -0.1000 15.24 1.039 -0.1000 14.26 1.054 -0.1000 13.32 1.052 -0.1000 12.20 1.115 -0.1000 11.24 1.184 -0.1000 10.12 1.180 -0.1000 9.15 1.150 -0.1000 8.25 1.118 -0.1000 7.14 1.070 -0.1000 6.26 1.022 -0.1000 5.11 0.920 -0.1000 4.21 0.839 -0.1000 3.10 0.738 -0.1000 1.97 0.626 -0.1000 1.09 0.525 -0.1000 -0.04 0.339 -0.1000 -0.92 0.206 -0.1000 -2.02 0.087 -0.1000 -3.13 0.002 -0.1000 -3.97 -0.049 -0.1000 -5.12 -0.137 -0.1000 -6.02 -0.208 -0.1000 Tabulated from data in file CL00857.DAT & reduced using program Q02.00L Average Reynolds #: 200500 Number of angles of attack: 49 alpha / Cl / Cm -5.54 -0.097 -0.1000 -4.52 0.002 -0.1000 -3.49 0.104 -0.1000 -2.48 0.202 -0.1000 -1.49 0.286 -0.1000 -0.20 0.422 -0.1000 0.76 0.508 -0.1000 1.72 0.607 -0.1000 2.68 0.701 -0.1000 3.60 0.814 -0.1000 4.82 0.933 -0.1000 5.80 1.017 -0.1000 6.77 1.076 -0.1000 7.71 1.127 -0.1000 8.89 1.171 -0.1000 9.81 1.188 -0.1000 10.76 1.208 -0.1000 11.68 1.195 -0.1000 12.74 1.143 -0.1000 13.66 1.096 -0.1000 14.69 1.064 -0.1000 15.81 1.056 -0.1000 16.69 1.029 -0.1000 17.72 1.028 -0.1000 18.88 1.031 -0.1000 17.09 1.019 -0.1000 16.13 1.054 -0.1000 15.10 1.065 -0.1000 14.11 1.088 -0.1000 13.02 1.137 -0.1000 12.33 1.186 -0.1000 11.13 1.196 -0.1000 10.14 1.186 -0.1000 9.37 1.173 -0.1000 8.11 1.135 -0.1000 7.13 1.083 -0.1000 6.24 1.034 -0.1000 5.03 0.938 -0.1000 4.23 0.861 -0.1000 2.98 0.735 -0.1000 2.13 0.632 -0.1000 1.03 0.523 -0.1000 -0.10 0.420 -0.1000 -1.07 0.311 -0.1000 -2.03 0.232 -0.1000 -3.24 0.112 -0.1000 -4.17 0.020 -0.1000 -5.09 -0.070 -0.1000 -6.25 -0.185 -0.1000 Tabulated from data in file CL00859.DAT & reduced using program Q02.00L Average Reynolds #: 300800 Number of angles of attack: 49 alpha / Cl / Cm -6.04 -0.168 -0.1000 -4.30 0.007 -0.1000 -3.53 0.086 -0.1000 -2.40 0.192 -0.1000 -1.40 0.301 -0.1000 -0.44 0.412 -0.1000 0.61 0.515 -0.1000 1.67 0.616 -0.1000 2.78 0.732 -0.1000 3.59 0.815 -0.1000 4.76 0.929 -0.1000 5.85 1.018 -0.1000 6.93 1.093 -0.1000 7.72 1.140 -0.1000 8.82 1.183 -0.1000 9.69 1.201 -0.1000 10.79 1.240 -0.1000 11.82 1.237 -0.1000 12.63 1.218 -0.1000 13.73 1.169 -0.1000 14.59 1.106 -0.1000 15.60 1.051 -0.1000 16.56 1.029 -0.1000 17.60 1.000 -0.1000 18.56 1.039 -0.1000 17.21 1.016 -0.1000 16.16 1.038 -0.1000 15.21 1.067 -0.1000 14.19 1.131 -0.1000 13.19 1.192 -0.1000 12.24 1.208 -0.1000 11.32 1.229 -0.1000 10.16 1.206 -0.1000 9.04 1.183 -0.1000 8.25 1.158 -0.1000 7.08 1.096 -0.1000 6.17 1.035 -0.1000 5.23 0.964 -0.1000 4.20 0.872 -0.1000 3.13 0.764 -0.1000 2.07 0.653 -0.1000 0.93 0.540 -0.1000 -0.21 0.431 -0.1000 -1.01 0.356 -0.1000 -2.20 0.209 -0.1000 -3.10 0.126 -0.1000 -4.22 0.014 -0.1000 -5.26 -0.089 -0.1000 -6.37 -0.198 -0.1000 Tabulated from data in file CL00861.DAT & reduced using program Q02.00L File s7012bf5.lft created on 09-12-1997 at 13:46:18 using program FORMAT :::::::::::::: S7012F10.LFT :::::::::::::: Airfoil: S7012 (B) Builder: M. Lachowski Comment: clean: flap = 10 degs Number of Reynolds #'s: 4 Average Reynolds #: 60000 Number of angles of attack: 49 alpha / Cl / Cm -6.14 -0.190 -0.1200 -4.62 -0.058 -0.1200 -3.39 0.039 -0.1200 -2.51 0.104 -0.1200 -1.60 0.198 -0.1200 -0.35 0.335 -0.1200 0.59 0.430 -0.1200 1.55 0.593 -0.1200 2.74 0.781 -0.1200 3.62 0.869 -0.1200 4.86 0.963 -0.1200 5.82 1.028 -0.1200 6.74 1.078 -0.1200 7.66 1.110 -0.1200 8.88 1.158 -0.1200 9.83 1.176 -0.1200 10.69 1.181 -0.1200 11.71 1.162 -0.1200 12.61 1.104 -0.1200 13.80 1.064 -0.1200 14.66 1.063 -0.1200 15.82 1.077 -0.1200 16.86 1.084 -0.1200 17.78 1.085 -0.1200 18.71 1.067 -0.1200 17.04 1.071 -0.1200 16.27 1.079 -0.1200 15.20 1.054 -0.1200 14.15 1.093 -0.1200 13.22 1.091 -0.1200 12.10 1.119 -0.1200 11.22 1.175 -0.1200 10.10 1.174 -0.1200 9.26 1.164 -0.1200 8.34 1.134 -0.1200 7.12 1.085 -0.1200 6.17 1.043 -0.1200 5.24 0.984 -0.1200 4.07 0.891 -0.1200 3.19 0.811 -0.1200 2.04 0.658 -0.1200 1.10 0.485 -0.1200 -0.01 0.345 -0.1200 -1.09 0.234 -0.1200 -2.02 0.135 -0.1200 -3.16 0.031 -0.1200 -4.11 -0.036 -0.1200 -5.04 -0.108 -0.1200 -6.12 -0.206 -0.1200 Tabulated from data in file CN00863.DAT & reduced using program Q02.00L Average Reynolds #: 100100 Number of angles of attack: 49 alpha / Cl / Cm -6.11 -0.087 -0.1200 -4.52 0.065 -0.1200 -3.56 0.139 -0.1200 -2.30 0.223 -0.1200 -1.52 0.253 -0.1200 -0.40 0.360 -0.1200 0.58 0.525 -0.1200 1.80 0.716 -0.1200 2.59 0.805 -0.1200 3.80 0.905 -0.1200 4.72 0.988 -0.1200 5.64 1.069 -0.1200 6.87 1.126 -0.1200 7.79 1.156 -0.1200 8.71 1.191 -0.1200 9.80 1.219 -0.1200 10.69 1.225 -0.1200 11.85 1.221 -0.1200 12.79 1.089 -0.1200 13.79 1.097 -0.1200 14.69 1.075 -0.1200 15.89 1.075 -0.1200 16.85 1.054 -0.1200 17.79 1.061 -0.1200 18.73 1.076 -0.1200 16.95 1.072 -0.1200 16.14 1.082 -0.1200 15.25 1.073 -0.1200 14.23 1.103 -0.1200 13.24 1.088 -0.1200 12.09 1.200 -0.1200 11.37 1.206 -0.1200 10.15 1.221 -0.1200 9.31 1.204 -0.1200 8.30 1.171 -0.1200 7.09 1.125 -0.1200 6.19 1.094 -0.1200 5.19 1.021 -0.1200 4.21 0.931 -0.1200 3.01 0.828 -0.1200 2.05 0.731 -0.1200 1.07 0.593 -0.1200 0.09 0.428 -0.1200 -0.94 0.295 -0.1200 -2.01 0.219 -0.1200 -2.98 0.168 -0.1200 -4.10 0.094 -0.1200 -5.15 0.010 -0.1200 -6.19 -0.083 -0.1200 Tabulated from data in file CN00865.DAT & reduced using program Q02.00L Average Reynolds #: 200400 Number of angles of attack: 49 alpha / Cl / Cm -5.73 -0.007 -0.1200 -4.42 0.127 -0.1200 -3.36 0.232 -0.1200 -2.26 0.334 -0.1200 -1.41 0.400 -0.1200 -0.36 0.506 -0.1200 0.66 0.621 -0.1200 1.67 0.719 -0.1200 2.77 0.841 -0.1200 3.79 0.940 -0.1200 4.82 1.030 -0.1200 5.92 1.096 -0.1200 6.87 1.143 -0.1200 7.89 1.184 -0.1200 8.77 1.208 -0.1200 9.73 1.227 -0.1200 10.83 1.225 -0.1200 11.73 1.222 -0.1200 12.65 1.195 -0.1200 13.69 1.155 -0.1200 14.67 1.117 -0.1200 15.83 1.065 -0.1200 16.82 1.060 -0.1200 17.75 1.072 -0.1200 18.78 1.064 -0.1200 16.78 1.047 -0.1200 16.14 1.078 -0.1200 15.17 1.098 -0.1200 14.09 1.107 -0.1200 13.06 1.171 -0.1200 12.23 1.204 -0.1200 11.27 1.243 -0.1200 10.04 1.237 -0.1200 9.16 1.212 -0.1200 8.10 1.185 -0.1200 7.31 1.156 -0.1200 6.15 1.103 -0.1200 5.11 1.045 -0.1200 4.10 0.963 -0.1200 3.04 0.860 -0.1200 2.00 0.760 -0.1200 1.08 0.655 -0.1200 -0.03 0.550 -0.1200 -1.07 0.426 -0.1200 -2.03 0.346 -0.1200 -3.10 0.252 -0.1200 -4.07 0.155 -0.1200 -5.07 0.054 -0.1200 -6.04 -0.043 -0.1200 Tabulated from data in file CN00867.DAT & reduced using program Q02.00L Average Reynolds #: 300500 Number of angles of attack: 49 alpha / Cl / Cm -6.06 -0.056 -0.1200 -4.44 0.109 -0.1200 -3.42 0.205 -0.1200 -2.54 0.298 -0.1200 -1.44 0.439 -0.1200 -0.52 0.530 -0.1200 0.64 0.642 -0.1200 1.57 0.727 -0.1200 2.81 0.848 -0.1200 3.57 0.921 -0.1200 4.67 1.019 -0.1200 5.94 1.102 -0.1200 6.77 1.149 -0.1200 7.86 1.198 -0.1200 8.80 1.228 -0.1200 9.75 1.252 -0.1200 10.66 1.257 -0.1200 11.69 1.270 -0.1200 12.67 1.257 -0.1200 13.53 1.215 -0.1200 14.61 1.125 -0.1200 15.53 1.100 -0.1200 16.58 1.072 -0.1200 17.45 1.059 -0.1200 18.45 1.090 -0.1200 17.33 1.054 -0.1200 16.20 1.069 -0.1200 15.16 1.087 -0.1200 14.21 1.120 -0.1200 13.21 1.207 -0.1200 12.18 1.256 -0.1200 11.12 1.252 -0.1200 10.44 1.270 -0.1200 9.14 1.228 -0.1200 8.20 1.205 -0.1200 7.00 1.157 -0.1200 6.01 1.103 -0.1200 5.20 1.054 -0.1200 3.84 0.944 -0.1200 3.17 0.880 -0.1200 2.05 0.766 -0.1200 1.08 0.677 -0.1200 -0.03 0.569 -0.1200 -1.11 0.467 -0.1200 -2.14 0.360 -0.1200 -2.94 0.252 -0.1200 -4.31 0.119 -0.1200 -5.08 0.044 -0.1200 -6.26 -0.074 -0.1200 Tabulated from data in file CL00869.DAT & reduced using program Q02.00L File s7012f10.lft created on 09-12-1997 at 13:46:18 using program FORMAT :::::::::::::: S7055GF1.LFT :::::::::::::: Airfoil: S7055 Builder: G. Jones Comment: gurney flap (h/c = 1.0%) Number of Reynolds #'s: 2 Average Reynolds #: 100000 Number of angles of attack: 51 alpha / Cl / Cm -3.23 0.184 -0.0680 -1.98 0.310 -0.0680 -0.88 0.362 -0.0680 -0.07 0.447 -0.0680 1.24 0.581 -0.0680 2.03 0.664 -0.0680 3.03 0.772 -0.0680 4.06 0.882 -0.0680 5.11 0.990 -0.0680 6.17 1.094 -0.0680 7.20 1.190 -0.0680 8.25 1.271 -0.0680 9.13 1.322 -0.0680 10.18 1.340 -0.0680 11.18 1.346 -0.0680 12.17 1.340 -0.0680 13.15 1.341 -0.0680 14.14 1.329 -0.0680 15.27 1.327 -0.0680 16.34 1.314 -0.0680 17.22 1.316 -0.0680 18.23 1.314 -0.0680 19.11 1.313 -0.0680 20.26 1.137 -0.0680 21.33 1.167 -0.0680 22.14 1.205 -0.0680 20.49 1.162 -0.0680 19.53 1.148 -0.0680 18.56 1.165 -0.0680 17.45 1.191 -0.0680 16.58 1.298 -0.0680 15.56 1.337 -0.0680 14.70 1.313 -0.0680 13.46 1.321 -0.0680 12.51 1.322 -0.0680 11.69 1.334 -0.0680 10.54 1.332 -0.0680 9.65 1.329 -0.0680 8.45 1.277 -0.0680 7.57 1.208 -0.0680 6.66 1.126 -0.0680 5.40 1.001 -0.0680 4.47 0.909 -0.0680 3.25 0.783 -0.0680 2.33 0.686 -0.0680 1.44 0.596 -0.0680 0.22 0.473 -0.0680 -0.66 0.377 -0.0680 -1.56 0.303 -0.0680 -2.79 0.247 -0.0680 -3.75 0.108 -0.0680 Tabulated from data in file AG00908.DAT & reduced using program Q02.00L Average Reynolds #: 300100 Number of angles of attack: 51 alpha / Cl / Cm -3.51 0.184 -0.0680 -2.24 0.356 -0.0680 -1.22 0.470 -0.0680 0.09 0.552 -0.0680 0.91 0.598 -0.0680 1.94 0.714 -0.0680 3.07 0.844 -0.0680 3.94 0.943 -0.0680 5.09 1.069 -0.0680 6.25 1.186 -0.0680 7.16 1.263 -0.0680 8.08 1.322 -0.0680 9.27 1.357 -0.0680 10.30 1.368 -0.0680 11.31 1.370 -0.0680 12.18 1.363 -0.0680 13.14 1.355 -0.0680 14.35 1.320 -0.0680 15.04 1.315 -0.0680 16.02 1.258 -0.0680 16.95 1.246 -0.0680 17.84 1.220 -0.0680 18.81 1.222 -0.0680 19.82 1.199 -0.0680 20.82 1.214 -0.0680 21.80 1.223 -0.0680 20.62 1.208 -0.0680 19.75 1.205 -0.0680 18.61 1.234 -0.0680 17.66 1.253 -0.0680 16.76 1.254 -0.0680 15.66 1.314 -0.0680 14.80 1.313 -0.0680 13.44 1.339 -0.0680 12.52 1.357 -0.0680 11.39 1.362 -0.0680 10.53 1.360 -0.0680 9.48 1.351 -0.0680 8.62 1.333 -0.0680 7.60 1.285 -0.0680 6.54 1.203 -0.0680 5.46 1.102 -0.0680 4.42 0.991 -0.0680 3.37 0.876 -0.0680 2.36 0.763 -0.0680 1.36 0.649 -0.0680 0.17 0.545 -0.0680 -0.78 0.503 -0.0680 -1.63 0.435 -0.0680 -2.64 0.311 -0.0680 -3.52 0.188 -0.0680 Tabulated from data in file AG00910.DAT & reduced using program Q02.00L File s7055gf1.lft created on 09-12-1997 at 13:46:18 using program FORMAT :::::::::::::: S7055GF4.LFT :::::::::::::: Airfoil: S7055 Builder: G. Jones Comment: gurney flap (h/c = 0.4%) Number of Reynolds #'s: 4 Average Reynolds #: 60200 Number of angles of attack: 51 alpha / Cl / Cm -3.68 -0.016 -0.0680 -2.16 0.125 -0.0680 -1.13 0.204 -0.0680 -0.13 0.313 -0.0680 0.88 0.428 -0.0680 2.17 0.575 -0.0680 2.95 0.656 -0.0680 4.01 0.766 -0.0680 5.09 0.876 -0.0680 6.16 0.979 -0.0680 7.18 1.077 -0.0680 8.26 1.165 -0.0680 9.31 1.236 -0.0680 10.11 1.275 -0.0680 11.11 1.285 -0.0680 12.39 1.295 -0.0680 13.10 1.302 -0.0680 14.29 1.286 -0.0680 15.23 1.262 -0.0680 16.20 1.261 -0.0680 17.21 1.169 -0.0680 18.07 1.103 -0.0680 19.39 1.108 -0.0680 20.12 1.100 -0.0680 21.17 1.113 -0.0680 22.20 1.116 -0.0680 20.63 1.128 -0.0680 19.69 1.164 -0.0680 18.49 1.154 -0.0680 17.60 1.171 -0.0680 16.74 1.291 -0.0680 15.63 1.331 -0.0680 14.56 1.320 -0.0680 13.71 1.347 -0.0680 12.59 1.353 -0.0680 11.77 1.353 -0.0680 10.63 1.338 -0.0680 9.73 1.301 -0.0680 8.53 1.222 -0.0680 7.62 1.151 -0.0680 6.69 1.064 -0.0680 5.47 0.953 -0.0680 4.56 0.856 -0.0680 3.41 0.732 -0.0680 2.38 0.612 -0.0680 1.48 0.519 -0.0680 0.45 0.405 -0.0680 -0.71 0.278 -0.0680 -1.58 0.201 -0.0680 -2.76 0.101 -0.0680 -3.68 -0.010 -0.0680 Tabulated from data in file PG00891.DAT & reduced using program Q02.00L Average Reynolds #: 100300 Number of angles of attack: 51 alpha / Cl / Cm -3.61 0.024 -0.0680 -2.00 0.211 -0.0680 -0.94 0.277 -0.0680 -0.16 0.356 -0.0680 1.15 0.491 -0.0680 1.96 0.568 -0.0680 3.14 0.692 -0.0680 4.20 0.802 -0.0680 5.28 0.911 -0.0680 6.05 0.988 -0.0680 7.11 1.087 -0.0680 8.18 1.176 -0.0680 9.26 1.243 -0.0680 10.31 1.264 -0.0680 11.34 1.268 -0.0680 12.07 1.262 -0.0680 13.28 1.263 -0.0680 14.27 1.255 -0.0680 15.24 1.247 -0.0680 16.24 1.236 -0.0680 17.27 1.106 -0.0680 18.19 1.065 -0.0680 19.29 1.050 -0.0680 20.07 1.059 -0.0680 21.30 1.065 -0.0680 22.31 1.077 -0.0680 20.53 1.086 -0.0680 19.51 1.052 -0.0680 18.63 1.079 -0.0680 17.65 1.112 -0.0680 16.43 1.123 -0.0680 15.75 1.183 -0.0680 14.47 1.249 -0.0680 13.73 1.263 -0.0680 12.57 1.268 -0.0680 11.59 1.277 -0.0680 10.68 1.275 -0.0680 9.47 1.263 -0.0680 8.53 1.215 -0.0680 7.60 1.141 -0.0680 6.62 1.057 -0.0680 5.63 0.961 -0.0680 4.41 0.837 -0.0680 3.49 0.740 -0.0680 2.52 0.641 -0.0680 1.29 0.519 -0.0680 0.37 0.424 -0.0680 -0.57 0.326 -0.0680 -1.54 0.236 -0.0680 -2.81 0.148 -0.0680 -3.76 0.036 -0.0680 Tabulated from data in file PG00893.DAT & reduced using program Q02.00L Average Reynolds #: 200400 Number of angles of attack: 51 alpha / Cl / Cm -3.79 0.064 -0.0680 -2.06 0.236 -0.0680 -0.77 0.327 -0.0680 -0.05 0.370 -0.0680 1.07 0.490 -0.0680 2.19 0.616 -0.0680 3.17 0.724 -0.0680 4.23 0.843 -0.0680 5.02 0.927 -0.0680 6.05 1.030 -0.0680 7.16 1.130 -0.0680 8.25 1.212 -0.0680 9.30 1.255 -0.0680 10.34 1.266 -0.0680 11.11 1.270 -0.0680 12.40 1.270 -0.0680 13.26 1.267 -0.0680 14.28 1.247 -0.0680 15.28 1.227 -0.0680 16.00 1.225 -0.0680 17.13 1.156 -0.0680 18.28 1.141 -0.0680 19.09 1.120 -0.0680 20.06 1.127 -0.0680 21.11 1.121 -0.0680 22.13 1.122 -0.0680 20.35 1.083 -0.0680 19.40 1.088 -0.0680 18.34 1.145 -0.0680 17.41 1.154 -0.0680 16.43 1.168 -0.0680 15.63 1.215 -0.0680 14.58 1.246 -0.0680 13.52 1.266 -0.0680 12.45 1.271 -0.0680 11.55 1.273 -0.0680 10.63 1.270 -0.0680 9.48 1.262 -0.0680 8.62 1.229 -0.0680 7.57 1.160 -0.0680 6.51 1.067 -0.0680 5.47 0.963 -0.0680 4.43 0.855 -0.0680 3.38 0.741 -0.0680 2.34 0.623 -0.0680 1.29 0.508 -0.0680 0.23 0.395 -0.0680 -0.56 0.332 -0.0680 -1.88 0.254 -0.0680 -2.70 0.170 -0.0680 -3.88 0.058 -0.0680 Tabulated from data in file PG00896.DAT & reduced using program Q02.00L Average Reynolds #: 300200 Number of angles of attack: 51 alpha / Cl / Cm -3.71 0.054 -0.0680 -2.19 0.214 -0.0680 -0.98 0.342 -0.0680 -0.15 0.375 -0.0680 0.89 0.475 -0.0680 2.06 0.609 -0.0680 3.07 0.723 -0.0680 4.11 0.838 -0.0680 5.15 0.951 -0.0680 6.20 1.056 -0.0680 7.26 1.150 -0.0680 8.26 1.222 -0.0680 9.40 1.265 -0.0680 10.23 1.274 -0.0680 11.22 1.286 -0.0680 12.32 1.282 -0.0680 13.12 1.280 -0.0680 14.24 1.263 -0.0680 15.08 1.242 -0.0680 15.96 1.244 -0.0680 17.09 1.176 -0.0680 18.01 1.156 -0.0680 18.99 1.142 -0.0680 19.95 1.123 -0.0680 20.85 1.121 -0.0680 21.84 1.140 -0.0680 20.58 1.115 -0.0680 19.57 1.122 -0.0680 18.59 1.156 -0.0680 17.69 1.162 -0.0680 16.61 1.192 -0.0680 15.69 1.242 -0.0680 14.54 1.260 -0.0680 13.54 1.277 -0.0680 12.60 1.285 -0.0680 11.52 1.284 -0.0680 10.63 1.281 -0.0680 9.55 1.268 -0.0680 8.41 1.231 -0.0680 7.37 1.158 -0.0680 6.45 1.082 -0.0680 5.27 0.963 -0.0680 4.38 0.870 -0.0680 3.24 0.742 -0.0680 2.43 0.652 -0.0680 1.32 0.526 -0.0680 0.33 0.416 -0.0680 -0.85 0.348 -0.0680 -1.60 0.285 -0.0680 -2.75 0.160 -0.0680 -3.81 0.053 -0.0680 Tabulated from data in file PG00898.DAT & reduced using program Q02.00L File s7055gf4.lft created on 09-12-1997 at 13:46:18 using program FORMAT :::::::::::::: S8025.LFT :::::::::::::: Airfoil: S8025 Builder: J. Thurmond Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60300 Number of angles of attack: 49 alpha / Cl / Cm -6.87 -0.596 -0.0030 -5.34 -0.477 -0.0030 -4.30 -0.401 -0.0030 -3.48 -0.329 -0.0030 -2.41 -0.212 -0.0030 -1.28 -0.073 -0.0030 -0.40 -0.010 -0.0030 0.87 0.123 -0.0030 1.78 0.221 -0.0030 2.69 0.321 -0.0030 3.83 0.428 -0.0030 4.98 0.533 -0.0030 5.93 0.615 -0.0030 6.84 0.691 -0.0030 7.99 0.785 -0.0030 8.88 0.846 -0.0030 10.01 0.848 -0.0030 10.86 0.846 -0.0030 11.95 0.864 -0.0030 12.83 0.853 -0.0030 13.98 0.863 -0.0030 14.93 0.879 -0.0030 15.94 0.889 -0.0030 17.00 0.894 -0.0030 17.97 0.888 -0.0030 16.39 0.911 -0.0030 15.56 0.879 -0.0030 14.45 0.858 -0.0030 13.44 0.877 -0.0030 12.37 0.872 -0.0030 11.48 0.843 -0.0030 10.29 0.824 -0.0030 9.54 0.824 -0.0030 8.45 0.809 -0.0030 7.43 0.728 -0.0030 6.36 0.642 -0.0030 5.32 0.553 -0.0030 4.25 0.453 -0.0030 3.23 0.362 -0.0030 2.40 0.278 -0.0030 1.28 0.153 -0.0030 0.25 0.036 -0.0030 -0.75 -0.050 -0.0030 -1.74 -0.154 -0.0030 -3.02 -0.304 -0.0030 -3.77 -0.377 -0.0030 -4.90 -0.475 -0.0030 -5.97 -0.561 -0.0030 -7.07 -0.646 -0.0030 Tabulated from data in file CF00875.DAT & reduced using program Q02.00L Average Reynolds #: 100600 Number of angles of attack: 49 alpha / Cl / Cm -6.51 -0.608 -0.0030 -5.47 -0.523 -0.0030 -4.26 -0.418 -0.0030 -3.33 -0.333 -0.0030 -2.16 -0.221 -0.0030 -1.24 -0.098 -0.0030 -0.18 -0.003 -0.0030 0.65 0.077 -0.0030 1.81 0.218 -0.0030 2.73 0.300 -0.0030 3.90 0.411 -0.0030 4.85 0.503 -0.0030 6.03 0.615 -0.0030 7.01 0.701 -0.0030 7.97 0.779 -0.0030 8.90 0.846 -0.0030 10.10 0.910 -0.0030 10.94 0.838 -0.0030 11.97 0.843 -0.0030 12.88 0.849 -0.0030 14.03 0.845 -0.0030 14.96 0.840 -0.0030 15.87 0.838 -0.0030 17.09 0.838 -0.0030 17.99 0.843 -0.0030 16.46 0.844 -0.0030 15.44 0.824 -0.0030 14.31 0.835 -0.0030 13.51 0.825 -0.0030 12.42 0.832 -0.0030 11.35 0.833 -0.0030 10.33 0.875 -0.0030 9.28 0.860 -0.0030 8.43 0.799 -0.0030 7.38 0.712 -0.0030 6.30 0.620 -0.0030 5.19 0.522 -0.0030 4.38 0.448 -0.0030 3.30 0.344 -0.0030 2.23 0.247 -0.0030 1.20 0.148 -0.0030 0.17 0.021 -0.0030 -0.83 -0.059 -0.0030 -1.84 -0.181 -0.0030 -2.91 -0.303 -0.0030 -3.95 -0.395 -0.0030 -5.02 -0.485 -0.0030 -5.97 -0.565 -0.0030 -7.05 -0.648 -0.0030 Tabulated from data in file CF00877.DAT & reduced using program Q02.00L Average Reynolds #: 201500 Number of angles of attack: 49 alpha / Cl / Cm -6.85 -0.637 -0.0030 -5.34 -0.507 -0.0030 -4.33 -0.413 -0.0030 -3.35 -0.320 -0.0030 -2.38 -0.228 -0.0030 -1.26 -0.116 -0.0030 -0.11 0.029 -0.0030 0.87 0.126 -0.0030 1.98 0.221 -0.0030 2.83 0.307 -0.0030 3.78 0.404 -0.0030 4.98 0.525 -0.0030 5.90 0.629 -0.0030 6.96 0.731 -0.0030 7.87 0.812 -0.0030 9.00 0.904 -0.0030 9.97 0.961 -0.0030 10.83 0.914 -0.0030 12.11 0.884 -0.0030 13.07 0.863 -0.0030 13.94 0.872 -0.0030 14.95 0.854 -0.0030 15.86 0.839 -0.0030 16.92 0.856 -0.0030 17.97 0.849 -0.0030 16.19 0.848 -0.0030 15.28 0.843 -0.0030 14.25 0.860 -0.0030 13.51 0.877 -0.0030 12.31 0.875 -0.0030 11.34 0.902 -0.0030 10.45 0.976 -0.0030 9.43 0.924 -0.0030 8.46 0.852 -0.0030 7.48 0.766 -0.0030 6.32 0.657 -0.0030 5.40 0.564 -0.0030 4.29 0.442 -0.0030 3.38 0.352 -0.0030 2.18 0.229 -0.0030 1.06 0.125 -0.0030 0.21 0.051 -0.0030 -0.91 -0.082 -0.0030 -1.97 -0.201 -0.0030 -2.81 -0.281 -0.0030 -3.96 -0.390 -0.0030 -4.98 -0.484 -0.0030 -5.87 -0.564 -0.0030 -7.11 -0.665 -0.0030 Tabulated from data in file CF00879.DAT & reduced using program Q02.00L Average Reynolds #: 302000 Number of angles of attack: 49 alpha / Cl / Cm -6.50 -0.618 -0.0030 -5.20 -0.503 -0.0030 -4.34 -0.420 -0.0030 -3.37 -0.326 -0.0030 -2.32 -0.221 -0.0030 -1.29 -0.119 -0.0030 -0.27 0.004 -0.0030 1.04 0.122 -0.0030 1.75 0.192 -0.0030 2.83 0.320 -0.0030 3.75 0.418 -0.0030 4.92 0.536 -0.0030 5.86 0.625 -0.0030 6.98 0.735 -0.0030 7.84 0.812 -0.0030 9.05 0.916 -0.0030 9.94 0.973 -0.0030 10.93 1.007 -0.0030 11.91 0.928 -0.0030 12.88 0.888 -0.0030 14.03 0.875 -0.0030 14.83 0.860 -0.0030 15.95 0.851 -0.0030 16.97 0.843 -0.0030 17.90 0.868 -0.0030 16.17 0.844 -0.0030 15.47 0.857 -0.0030 14.34 0.871 -0.0030 13.44 0.899 -0.0030 12.30 0.915 -0.0030 11.32 0.955 -0.0030 10.63 0.998 -0.0030 9.40 0.936 -0.0030 8.42 0.860 -0.0030 7.39 0.768 -0.0030 6.29 0.661 -0.0030 5.41 0.575 -0.0030 4.24 0.458 -0.0030 3.28 0.359 -0.0030 2.37 0.266 -0.0030 1.29 0.140 -0.0030 0.13 0.038 -0.0030 -0.70 -0.055 -0.0030 -1.84 -0.179 -0.0030 -3.05 -0.300 -0.0030 -3.95 -0.386 -0.0030 -4.90 -0.479 -0.0030 -6.12 -0.589 -0.0030 -7.13 -0.673 -0.0030 Tabulated from data in file AG00881.DAT & reduced using program Q02.00L File s8025.lft created on 09-12-1997 at 13:46:18 using program FORMAT :::::::::::::: S822.LFT :::::::::::::: Airfoil: S822 Builder: M. Allen Comment: clean Number of Reynolds #'s: 1 Average Reynolds #: 101200 Number of angles of attack: 49 alpha / Cl / Cm -6.30 -0.547 -0.0700 -4.94 -0.383 -0.0700 -3.95 -0.320 -0.0700 -2.94 -0.245 -0.0700 -2.02 -0.223 -0.0700 -0.83 -0.174 -0.0700 0.15 -0.083 -0.0700 1.14 -0.002 -0.0700 2.14 0.081 -0.0700 3.15 0.172 -0.0700 4.16 0.274 -0.0700 5.19 0.396 -0.0700 6.28 0.709 -0.0700 7.34 0.902 -0.0700 8.43 0.985 -0.0700 9.32 1.042 -0.0700 10.45 1.061 -0.0700 11.39 1.080 -0.0700 12.45 1.109 -0.0700 13.37 1.124 -0.0700 14.39 1.130 -0.0700 15.44 1.117 -0.0700 16.26 0.795 -0.0700 17.31 0.793 -0.0700 18.30 0.807 -0.0700 17.01 0.794 -0.0700 15.98 0.811 -0.0700 14.96 0.904 -0.0700 14.03 1.125 -0.0700 12.99 1.115 -0.0700 12.05 1.098 -0.0700 11.09 1.071 -0.0700 10.09 1.060 -0.0700 9.05 1.025 -0.0700 7.93 0.953 -0.0700 7.05 0.863 -0.0700 5.90 0.540 -0.0700 4.79 0.319 -0.0700 3.89 0.235 -0.0700 2.73 0.123 -0.0700 1.87 0.043 -0.0700 0.73 -0.052 -0.0700 -0.26 -0.135 -0.0700 -1.25 -0.209 -0.0700 -2.22 -0.237 -0.0700 -3.31 -0.282 -0.0700 -4.29 -0.349 -0.0700 -5.26 -0.410 -0.0700 -6.35 -0.545 -0.0700 Tabulated from data in file CL00728.DAT & reduced using program Q02.00L File s822.lft created on 09-12-1997 at 13:46:18 using program FORMAT :::::::::::::: S822T1.LFT :::::::::::::: Airfoil: S822 Builder: M. Allen Comment: Zig-Zag trip type "C" @ x/c = 2% u.s. & 5% l.s. (h/c = 0.19%) Number of Reynolds #'s: 4 Average Reynolds #: 101200 Number of angles of attack: 49 alpha / Cl / Cm -6.33 -0.583 -0.0700 -4.81 -0.382 -0.0700 -3.96 -0.322 -0.0700 -2.76 -0.195 -0.0700 -1.89 -0.128 -0.0700 -0.83 -0.040 -0.0700 0.21 0.032 -0.0700 1.26 0.090 -0.0700 2.31 0.194 -0.0700 3.24 0.555 -0.0700 4.28 0.599 -0.0700 5.33 0.610 -0.0700 6.42 0.698 -0.0700 7.30 0.761 -0.0700 8.34 0.828 -0.0700 9.39 0.888 -0.0700 10.39 0.943 -0.0700 11.39 0.991 -0.0700 12.37 1.043 -0.0700 13.37 1.096 -0.0700 14.35 1.129 -0.0700 15.47 0.822 -0.0700 16.38 0.749 -0.0700 17.46 0.766 -0.0700 18.41 0.805 -0.0700 16.94 0.751 -0.0700 16.05 0.852 -0.0700 14.97 0.819 -0.0700 14.08 0.931 -0.0700 12.95 1.074 -0.0700 12.13 1.026 -0.0700 11.01 0.968 -0.0700 10.02 0.917 -0.0700 9.02 0.859 -0.0700 8.02 0.801 -0.0700 7.00 0.730 -0.0700 5.92 0.649 -0.0700 4.89 0.587 -0.0700 3.88 0.583 -0.0700 2.87 0.479 -0.0700 1.77 0.123 -0.0700 0.84 0.052 -0.0700 -0.24 -0.001 -0.0700 -1.20 -0.075 -0.0700 -2.31 -0.155 -0.0700 -3.27 -0.228 -0.0700 -4.27 -0.343 -0.0700 -5.37 -0.451 -0.0700 -6.42 -0.565 -0.0700 Tabulated from data in file PG00826.DAT & reduced using program Q02.00L Average Reynolds #: 201900 Number of angles of attack: 49 alpha / Cl / Cm -6.43 -0.360 -0.0700 -4.73 -0.206 -0.0700 -3.67 -0.115 -0.0700 -2.91 -0.046 -0.0700 -1.61 0.113 -0.0700 -0.67 0.213 -0.0700 0.38 0.297 -0.0700 1.35 0.369 -0.0700 2.30 0.447 -0.0700 3.28 0.526 -0.0700 4.52 0.607 -0.0700 5.23 0.639 -0.0700 6.37 0.702 -0.0700 7.28 0.775 -0.0700 8.40 0.848 -0.0700 9.52 0.912 -0.0700 10.38 0.956 -0.0700 11.43 1.006 -0.0700 12.48 1.051 -0.0700 13.56 1.090 -0.0700 14.52 1.123 -0.0700 15.48 1.143 -0.0700 16.48 1.166 -0.0700 17.13 0.777 -0.0700 18.47 0.830 -0.0700 16.91 0.908 -0.0700 15.96 0.869 -0.0700 14.90 0.909 -0.0700 14.10 1.107 -0.0700 13.01 1.070 -0.0700 12.11 1.030 -0.0700 11.06 0.983 -0.0700 9.99 0.932 -0.0700 8.88 0.870 -0.0700 7.99 0.816 -0.0700 6.85 0.736 -0.0700 5.92 0.665 -0.0700 4.94 0.627 -0.0700 3.93 0.572 -0.0700 2.90 0.493 -0.0700 1.87 0.407 -0.0700 0.82 0.329 -0.0700 -0.28 0.246 -0.0700 -1.39 0.136 -0.0700 -2.28 0.011 -0.0700 -3.47 -0.100 -0.0700 -4.30 -0.168 -0.0700 -5.49 -0.275 -0.0700 -6.43 -0.361 -0.0700 Tabulated from data in file PG00828.DAT & reduced using program Q02.00L Average Reynolds #: 302900 Number of angles of attack: 49 alpha / Cl / Cm -6.33 -0.306 -0.0700 -4.91 -0.183 -0.0700 -3.73 -0.079 -0.0700 -2.73 0.001 -0.0700 -1.76 0.082 -0.0700 -0.81 0.169 -0.0700 0.25 0.256 -0.0700 1.35 0.351 -0.0700 2.43 0.451 -0.0700 3.45 0.540 -0.0700 4.43 0.621 -0.0700 5.44 0.696 -0.0700 6.42 0.754 -0.0700 7.36 0.789 -0.0700 8.45 0.847 -0.0700 9.34 0.899 -0.0700 10.32 0.949 -0.0700 11.40 1.001 -0.0700 12.54 1.051 -0.0700 13.53 1.092 -0.0700 14.35 1.120 -0.0700 15.51 1.163 -0.0700 16.41 1.176 -0.0700 17.40 1.173 -0.0700 18.02 0.805 -0.0700 16.84 0.864 -0.0700 15.89 0.904 -0.0700 15.23 1.150 -0.0700 13.99 1.109 -0.0700 13.01 1.073 -0.0700 11.98 1.029 -0.0700 10.99 0.983 -0.0700 9.93 0.931 -0.0700 8.84 0.870 -0.0700 7.97 0.817 -0.0700 7.01 0.776 -0.0700 5.90 0.726 -0.0700 4.77 0.646 -0.0700 3.84 0.572 -0.0700 2.87 0.488 -0.0700 1.64 0.375 -0.0700 0.68 0.291 -0.0700 -0.41 0.201 -0.0700 -1.48 0.105 -0.0700 -2.54 0.015 -0.0700 -3.32 -0.044 -0.0700 -4.31 -0.130 -0.0700 -5.58 -0.241 -0.0700 -6.45 -0.315 -0.0700 Tabulated from data in file PG00830.DAT & reduced using program Q02.00L Average Reynolds #: 403900 Number of angles of attack: 33 alpha / Cl / Cm -2.29 0.025 -0.0700 -0.80 0.159 -0.0700 0.27 0.254 -0.0700 1.14 0.335 -0.0700 2.32 0.442 -0.0700 3.32 0.527 -0.0700 4.52 0.625 -0.0700 5.37 0.689 -0.0700 6.41 0.759 -0.0700 7.56 0.827 -0.0700 8.38 0.869 -0.0700 9.55 0.916 -0.0700 10.45 0.962 -0.0700 11.50 1.016 -0.0700 12.42 1.058 -0.0700 13.40 1.102 -0.0700 14.41 1.138 -0.0700 13.05 1.085 -0.0700 11.91 1.034 -0.0700 10.96 0.988 -0.0700 9.94 0.934 -0.0700 8.81 0.883 -0.0700 7.78 0.837 -0.0700 6.82 0.782 -0.0700 5.60 0.702 -0.0700 4.87 0.650 -0.0700 3.72 0.558 -0.0700 2.55 0.456 -0.0700 1.73 0.383 -0.0700 0.66 0.282 -0.0700 -0.40 0.188 -0.0700 -1.31 0.109 -0.0700 -2.56 -0.003 -0.0700 Tabulated from data in file PG00853.DAT & reduced using program Q02.00L File s822t1.lft created on 09-12-1997 at 13:46:18 using program FORMAT :::::::::::::: S822T2.LFT :::::::::::::: Airfoil: S822 Builder: M. Allen Comment: plain trip @ x/c = 2% u.s. & 5% l.s. (h/c = 0.19%; w/c = 1.0%) Number of Reynolds #'s: 1 Average Reynolds #: 100900 Number of angles of attack: 49 alpha / Cl / Cm -6.66 -0.631 -0.0700 -4.99 -0.458 -0.0700 -3.84 -0.313 -0.0700 -2.90 -0.239 -0.0700 -1.92 -0.149 -0.0700 -0.77 -0.084 -0.0700 0.23 -0.030 -0.0700 1.25 0.019 -0.0700 2.12 0.104 -0.0700 3.16 0.176 -0.0700 4.31 0.648 -0.0700 5.36 0.741 -0.0700 6.36 0.734 -0.0700 7.37 0.770 -0.0700 8.38 0.828 -0.0700 9.38 0.892 -0.0700 10.47 0.964 -0.0700 11.39 1.023 -0.0700 12.45 1.083 -0.0700 13.44 1.121 -0.0700 14.41 1.146 -0.0700 15.50 1.150 -0.0700 16.44 0.896 -0.0700 17.30 0.762 -0.0700 18.41 0.794 -0.0700 16.85 0.854 -0.0700 15.86 0.901 -0.0700 15.01 0.905 -0.0700 13.89 1.145 -0.0700 13.01 1.120 -0.0700 11.94 1.059 -0.0700 10.85 0.991 -0.0700 10.02 0.936 -0.0700 8.90 0.863 -0.0700 7.76 0.793 -0.0700 6.89 0.750 -0.0700 5.96 0.728 -0.0700 4.73 0.692 -0.0700 3.80 0.543 -0.0700 2.76 0.155 -0.0700 1.85 0.075 -0.0700 0.63 -0.021 -0.0700 -0.31 -0.058 -0.0700 -1.34 -0.107 -0.0700 -2.29 -0.176 -0.0700 -3.27 -0.271 -0.0700 -4.28 -0.349 -0.0700 -5.48 -0.502 -0.0700 -6.43 -0.594 -0.0700 Tabulated from data in file CL00731.DAT & reduced using program Q02.00L File s822t2.lft created on 09-12-1997 at 13:46:18 using program FORMAT :::::::::::::: S823T.LFT :::::::::::::: Airfoil: S823 Builder: M. Allen Comment: Zig-Zag trip type "C" @ x/c = 2% u.s. & 5% l.s. (h/c = 0.19%) Number of Reynolds #'s: 4 Average Reynolds #: 101300 Number of angles of attack: 49 alpha / Cl / Cm -5.95 -0.129 -0.1500 -4.58 -0.186 -0.1500 -3.52 -0.117 -0.1500 -2.42 0.027 -0.1500 -1.59 -0.034 -0.1500 -0.34 0.087 -0.1500 0.49 0.207 -0.1500 1.58 0.356 -0.1500 2.67 0.486 -0.1500 3.78 0.603 -0.1500 4.68 0.686 -0.1500 5.78 0.763 -0.1500 6.67 0.808 -0.1500 7.75 0.865 -0.1500 8.78 0.918 -0.1500 9.81 0.960 -0.1500 10.80 0.988 -0.1500 11.76 1.012 -0.1500 12.73 1.043 -0.1500 13.69 1.075 -0.1500 14.89 1.115 -0.1500 15.88 1.137 -0.1500 16.87 1.152 -0.1500 17.69 0.826 -0.1500 18.78 0.846 -0.1500 17.17 0.807 -0.1500 16.34 0.838 -0.1500 15.20 1.143 -0.1500 14.26 1.116 -0.1500 13.40 1.084 -0.1500 12.30 1.045 -0.1500 11.19 1.014 -0.1500 10.35 0.992 -0.1500 9.22 0.948 -0.1500 8.32 0.910 -0.1500 7.10 0.847 -0.1500 6.17 0.797 -0.1500 5.20 0.735 -0.1500 4.22 0.657 -0.1500 3.22 0.556 -0.1500 2.24 0.445 -0.1500 1.03 0.286 -0.1500 0.09 0.162 -0.1500 -0.90 0.028 -0.1500 -2.12 -0.105 -0.1500 -3.03 -0.195 -0.1500 -3.97 -0.264 -0.1500 -5.11 -0.408 -0.1500 -6.05 -0.494 -0.1500 Tabulated from data in file CL00729.DAT & reduced using program Q02.00L Average Reynolds #: 202600 Number of angles of attack: 49 alpha / Cl / Cm -5.91 -0.253 -0.1500 -4.43 -0.138 -0.1500 -3.44 -0.078 -0.1500 -2.44 0.000 -0.1500 -1.38 0.098 -0.1500 -0.32 0.202 -0.1500 0.72 0.301 -0.1500 1.71 0.387 -0.1500 2.63 0.462 -0.1500 3.64 0.547 -0.1500 4.83 0.648 -0.1500 5.78 0.721 -0.1500 6.83 0.796 -0.1500 7.87 0.862 -0.1500 8.91 0.921 -0.1500 9.92 0.957 -0.1500 10.67 0.985 -0.1500 11.89 1.026 -0.1500 12.74 1.046 -0.1500 13.85 1.076 -0.1500 14.82 1.094 -0.1500 15.84 1.121 -0.1500 16.86 1.145 -0.1500 17.85 1.142 -0.1500 18.52 0.793 -0.1500 17.35 1.156 -0.1500 16.33 1.142 -0.1500 15.29 1.110 -0.1500 14.17 1.087 -0.1500 13.34 1.059 -0.1500 12.36 1.036 -0.1500 11.30 1.003 -0.1500 10.23 0.966 -0.1500 9.15 0.924 -0.1500 8.30 0.882 -0.1500 7.08 0.806 -0.1500 6.15 0.743 -0.1500 5.20 0.671 -0.1500 4.23 0.592 -0.1500 2.99 0.487 -0.1500 2.07 0.408 -0.1500 1.11 0.332 -0.1500 -0.15 0.211 -0.1500 -1.06 0.120 -0.1500 -1.88 0.040 -0.1500 -3.09 -0.064 -0.1500 -4.01 -0.126 -0.1500 -4.98 -0.181 -0.1500 -6.16 -0.292 -0.1500 Tabulated from data in file PG00833.DAT & reduced using program Q02.00L Average Reynolds #: 303800 Number of angles of attack: 49 alpha / Cl / Cm -6.03 -0.265 -0.1500 -4.50 -0.171 -0.1500 -3.65 -0.114 -0.1500 -2.62 -0.037 -0.1500 -1.50 0.064 -0.1500 -0.41 0.174 -0.1500 0.60 0.266 -0.1500 1.50 0.346 -0.1500 2.64 0.450 -0.1500 3.53 0.533 -0.1500 4.72 0.637 -0.1500 5.69 0.714 -0.1500 6.68 0.784 -0.1500 7.70 0.847 -0.1500 8.73 0.899 -0.1500 9.93 0.948 -0.1500 10.72 0.980 -0.1500 11.73 1.016 -0.1500 12.72 1.046 -0.1500 13.73 1.073 -0.1500 14.73 1.115 -0.1500 15.69 1.131 -0.1500 16.92 1.141 -0.1500 17.69 1.140 -0.1500 18.83 1.137 -0.1500 17.17 1.130 -0.1500 16.27 1.134 -0.1500 15.22 1.122 -0.1500 14.26 1.099 -0.1500 13.12 1.066 -0.1500 12.17 1.033 -0.1500 11.23 0.998 -0.1500 10.26 0.964 -0.1500 9.26 0.923 -0.1500 8.17 0.868 -0.1500 7.04 0.803 -0.1500 6.21 0.746 -0.1500 5.09 0.661 -0.1500 4.15 0.582 -0.1500 3.09 0.487 -0.1500 1.94 0.378 -0.1500 1.07 0.305 -0.1500 -0.19 0.193 -0.1500 -1.15 0.098 -0.1500 -2.09 0.008 -0.1500 -3.04 -0.070 -0.1500 -4.17 -0.152 -0.1500 -5.02 -0.196 -0.1500 -6.15 -0.278 -0.1500 Tabulated from data in file PG00835.DAT & reduced using program Q02.00L Average Reynolds #: 404600 Number of angles of attack: 37 alpha / Cl / Cm -2.85 -0.065 -0.1500 -1.75 0.036 -0.1500 -0.76 0.128 -0.1500 0.26 0.222 -0.1500 1.28 0.333 -0.1500 2.38 0.445 -0.1500 3.44 0.550 -0.1500 4.46 0.639 -0.1500 5.54 0.716 -0.1500 6.62 0.792 -0.1500 7.53 0.846 -0.1500 8.59 0.899 -0.1500 9.64 0.947 -0.1500 10.69 0.981 -0.1500 11.65 1.015 -0.1500 12.65 1.048 -0.1500 13.63 1.062 -0.1500 14.60 1.079 -0.1500 15.69 1.085 -0.1500 14.13 1.071 -0.1500 13.15 1.049 -0.1500 12.22 1.032 -0.1500 11.30 1.004 -0.1500 10.10 0.965 -0.1500 9.28 0.935 -0.1500 8.25 0.887 -0.1500 7.19 0.828 -0.1500 6.28 0.773 -0.1500 5.18 0.698 -0.1500 4.17 0.618 -0.1500 3.23 0.528 -0.1500 2.25 0.438 -0.1500 1.10 0.316 -0.1500 0.16 0.214 -0.1500 -0.84 0.118 -0.1500 -1.93 0.018 -0.1500 -2.88 -0.073 -0.1500 Tabulated from data in file PG00734.DAT & reduced using program Q02.00L File s823t.lft created on 09-12-1997 at 13:46:18 using program FORMAT