XFOIL Version 6.96 Calculated polar for: LOCKHEED-GEORGIA SUPERCRITICAL AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.500 -0.5961 0.08243 0.08016 -0.0135 1.0000 0.0081 -9.250 -0.6131 0.07272 0.07045 -0.0237 1.0000 0.0079 -9.000 -0.6355 0.06574 0.06338 -0.0274 1.0000 0.0078 -8.750 -0.6500 0.05963 0.05713 -0.0283 1.0000 0.0078 -8.500 -0.6585 0.05392 0.05123 -0.0281 1.0000 0.0079 -8.250 -0.6645 0.04821 0.04527 -0.0267 1.0000 0.0079 -7.750 -0.7124 0.02654 0.02191 -0.0151 1.0000 0.0073 -7.500 -0.7016 0.02403 0.01905 -0.0124 1.0000 0.0073 -7.250 -0.6875 0.02223 0.01698 -0.0101 1.0000 0.0074 -7.000 -0.6716 0.02079 0.01530 -0.0080 1.0000 0.0076 -6.750 -0.6431 0.01927 0.01355 -0.0085 0.9979 0.0078 -6.500 -0.6131 0.01797 0.01204 -0.0092 0.9958 0.0080 -6.250 -0.5826 0.01683 0.01073 -0.0099 0.9937 0.0083 -6.000 -0.5528 0.01585 0.00959 -0.0105 0.9908 0.0087 -5.750 -0.5220 0.01502 0.00864 -0.0112 0.9881 0.0090 -5.500 -0.4899 0.01432 0.00784 -0.0122 0.9859 0.0092 -5.250 -0.4592 0.01349 0.00697 -0.0130 0.9831 0.0097 -5.000 -0.4292 0.01295 0.00640 -0.0136 0.9788 0.0101 -4.750 -0.3976 0.01248 0.00592 -0.0145 0.9751 0.0107 -4.500 -0.3657 0.01207 0.00547 -0.0154 0.9715 0.0116 -4.250 -0.3371 0.01167 0.00502 -0.0156 0.9646 0.0123 -4.000 -0.3064 0.01115 0.00450 -0.0162 0.9592 0.0132 -3.750 -0.2783 0.01080 0.00413 -0.0162 0.9500 0.0142 -3.500 -0.2495 0.01047 0.00375 -0.0161 0.9346 0.0154 -3.250 -0.2230 0.01015 0.00336 -0.0155 0.9114 0.0170 -3.000 -0.1972 0.00993 0.00308 -0.0148 0.8893 0.0196 -2.750 -0.1710 0.00970 0.00282 -0.0143 0.8724 0.0238 -2.500 -0.1449 0.00950 0.00258 -0.0137 0.8538 0.0315 -2.250 -0.1192 0.00925 0.00237 -0.0131 0.8338 0.0539 -2.000 -0.0938 0.00895 0.00217 -0.0126 0.8111 0.1002 -1.750 -0.0693 0.00855 0.00198 -0.0120 0.7868 0.1836 -1.500 -0.0468 0.00788 0.00177 -0.0112 0.7602 0.3434 -1.250 -0.0274 0.00698 0.00160 -0.0098 0.7308 0.5693 -1.000 -0.0057 0.00660 0.00155 -0.0084 0.6989 0.6913 -0.750 0.0164 0.00642 0.00157 -0.0068 0.6637 0.7828 -0.500 0.0389 0.00644 0.00163 -0.0052 0.6225 0.8470 -0.250 0.0633 0.00659 0.00167 -0.0041 0.5783 0.8780 0.000 0.0887 0.00679 0.00170 -0.0034 0.5319 0.8962 0.250 0.1144 0.00704 0.00174 -0.0028 0.4806 0.9094 0.500 0.1409 0.00729 0.00179 -0.0025 0.4343 0.9199 0.750 0.1676 0.00751 0.00183 -0.0022 0.3959 0.9300 1.000 0.1955 0.00775 0.00190 -0.0021 0.3604 0.9385 1.500 0.2532 0.00814 0.00203 -0.0026 0.3083 0.9531 1.750 0.2822 0.00833 0.00210 -0.0028 0.2875 0.9597 2.000 0.3138 0.00852 0.00218 -0.0037 0.2695 0.9642 2.500 0.3754 0.00885 0.00236 -0.0050 0.2426 0.9741 2.750 0.4082 0.00901 0.00245 -0.0062 0.2306 0.9772 3.000 0.4403 0.00918 0.00256 -0.0072 0.2211 0.9808 3.250 0.4714 0.00934 0.00268 -0.0080 0.2121 0.9846 3.500 0.5055 0.00950 0.00279 -0.0095 0.2032 0.9864 3.750 0.5389 0.00969 0.00292 -0.0108 0.1942 0.9887 4.000 0.5717 0.00984 0.00305 -0.0120 0.1871 0.9914 4.250 0.6034 0.01003 0.00320 -0.0130 0.1802 0.9942 4.500 0.6366 0.01018 0.00336 -0.0143 0.1736 0.9960 5.000 0.7016 0.01055 0.00369 -0.0167 0.1606 1.0000 5.250 0.7249 0.01073 0.00385 -0.0159 0.1554 1.0000 5.500 0.7479 0.01092 0.00403 -0.0150 0.1509 1.0000 5.750 0.7712 0.01108 0.00421 -0.0142 0.1462 1.0000 6.000 0.7943 0.01129 0.00440 -0.0134 0.1409 1.0000 6.250 0.8175 0.01151 0.00463 -0.0125 0.1367 1.0000 6.500 0.8410 0.01170 0.00485 -0.0117 0.1329 1.0000 6.750 0.8644 0.01193 0.00508 -0.0110 0.1288 1.0000 7.000 0.8874 0.01220 0.00536 -0.0101 0.1247 1.0000 7.250 0.9112 0.01241 0.00560 -0.0094 0.1209 1.0000 7.500 0.9347 0.01267 0.00586 -0.0087 0.1149 1.0000 7.750 0.9582 0.01295 0.00615 -0.0080 0.1102 1.0000 8.000 0.9823 0.01320 0.00645 -0.0074 0.1061 1.0000 8.250 1.0059 0.01352 0.00675 -0.0068 0.1009 1.0000 8.500 1.0298 0.01381 0.00708 -0.0063 0.0966 1.0000 8.750 1.0538 0.01412 0.00742 -0.0057 0.0916 1.0000 9.000 1.0771 0.01450 0.00780 -0.0052 0.0865 1.0000 9.250 1.1012 0.01481 0.00816 -0.0046 0.0819 1.0000 9.500 1.1243 0.01521 0.00857 -0.0041 0.0764 1.0000 9.750 1.1477 0.01559 0.00900 -0.0035 0.0710 1.0000 10.000 1.1701 0.01608 0.00948 -0.0029 0.0638 1.0000 10.250 1.1923 0.01658 0.00999 -0.0022 0.0561 1.0000 10.500 1.2135 0.01719 0.01059 -0.0015 0.0475 1.0000 10.750 1.2337 0.01790 0.01128 -0.0006 0.0394 1.0000 11.000 1.2535 0.01861 0.01202 0.0003 0.0340 1.0000 11.250 1.2725 0.01939 0.01282 0.0013 0.0300 1.0000 11.500 1.2921 0.02006 0.01357 0.0022 0.0272 1.0000 11.750 1.3097 0.02090 0.01446 0.0033 0.0245 1.0000 12.000 1.3280 0.02162 0.01527 0.0044 0.0227 1.0000 12.250 1.3450 0.02241 0.01615 0.0056 0.0209 1.0000 12.500 1.3596 0.02336 0.01717 0.0070 0.0193 1.0000 12.750 1.3746 0.02421 0.01811 0.0084 0.0181 1.0000 13.000 1.3874 0.02509 0.01909 0.0101 0.0170 1.0000 13.250 1.3965 0.02609 0.02017 0.0122 0.0160 1.0000 13.500 1.4029 0.02730 0.02147 0.0144 0.0151 1.0000 13.750 1.4095 0.02854 0.02282 0.0164 0.0144 1.0000 14.000 1.4162 0.02984 0.02426 0.0180 0.0138 1.0000 14.250 1.4209 0.03138 0.02591 0.0195 0.0132 1.0000 14.500 1.4232 0.03322 0.02786 0.0207 0.0126 1.0000 14.750 1.4229 0.03547 0.03023 0.0215 0.0121 1.0000 15.000 1.4192 0.03831 0.03320 0.0218 0.0117 1.0000 15.250 1.4113 0.04196 0.03699 0.0212 0.0114 1.0000 15.500 1.4049 0.04588 0.04108 0.0198 0.0112 1.0000 15.750 1.3935 0.05096 0.04634 0.0173 0.0111 1.0000 16.000 1.3761 0.05760 0.05317 0.0135 0.0110 1.0000 16.250 1.3497 0.06627 0.06205 0.0084 0.0110 1.0000 16.500 1.3133 0.07677 0.07275 0.0026 0.0112 1.0000 16.750 1.2706 0.08804 0.08419 -0.0030 0.0114 1.0000