XFOIL Version 6.96 Calculated polar for: FX 66-S-161 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.000 -0.3306 0.09569 0.09120 -0.0551 1.0000 0.0263 -10.750 -0.3413 0.08913 0.08473 -0.0581 1.0000 0.0261 -10.500 -0.3565 0.07818 0.07382 -0.0658 0.9638 0.0257 -10.250 -0.3931 0.06240 0.05776 -0.0830 0.9136 0.0240 -10.000 -0.4111 0.05302 0.04785 -0.0957 0.8703 0.0236 -9.500 -0.4199 0.04660 0.04075 -0.0999 0.8119 0.0246 -9.250 -0.4207 0.04398 0.03776 -0.0998 0.7937 0.0253 -9.000 -0.4186 0.04127 0.03464 -0.0994 0.7788 0.0259 -8.750 -0.4124 0.03860 0.03152 -0.0987 0.7661 0.0267 -8.500 -0.4014 0.03608 0.02852 -0.0980 0.7550 0.0272 -8.250 -0.3865 0.03378 0.02575 -0.0973 0.7454 0.0279 -8.000 -0.3684 0.03182 0.02336 -0.0966 0.7353 0.0286 -7.750 -0.3483 0.02998 0.02139 -0.0963 0.7268 0.0297 -7.500 -0.3272 0.02885 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0.01879 0.00965 -0.0872 0.6202 0.5551 -2.500 0.1464 0.01881 0.00956 -0.0871 0.6162 0.5643 -2.250 0.1738 0.01880 0.00941 -0.0871 0.6128 0.5717 -2.000 0.2019 0.01879 0.00922 -0.0872 0.6099 0.5782 -1.750 0.2284 0.01883 0.00921 -0.0871 0.6059 0.5841 -1.500 0.2555 0.01887 0.00915 -0.0872 0.6021 0.5914 -1.250 0.2825 0.01890 0.00911 -0.0871 0.5988 0.5971 -1.000 0.3105 0.01893 0.00901 -0.0873 0.5960 0.6039 -0.750 0.3376 0.01899 0.00902 -0.0873 0.5931 0.6096 -0.500 0.3637 0.01911 0.00913 -0.0872 0.5895 0.6161 -0.250 0.3906 0.01920 0.00918 -0.0873 0.5862 0.6231 0.000 0.4177 0.01927 0.00921 -0.0872 0.5832 0.6298 0.250 0.4458 0.01934 0.00920 -0.0874 0.5807 0.6378 0.500 0.4719 0.01948 0.00935 -0.0872 0.5777 0.6451 0.750 0.4973 0.01968 0.00959 -0.0871 0.5743 0.6532 1.000 0.5231 0.01983 0.00977 -0.0869 0.5713 0.6608 1.250 0.5500 0.01996 0.00988 -0.0869 0.5684 0.6689 1.500 0.5773 0.02005 0.00995 -0.0869 0.5660 0.6772 1.750 0.6038 0.02022 0.01014 -0.0869 0.5632 0.6860 2.000 0.6277 0.02050 0.01052 -0.0866 0.5594 0.6962 2.250 0.6529 0.02068 0.01076 -0.0863 0.5559 0.7066 2.500 0.6795 0.02078 0.01091 -0.0862 0.5528 0.7184 2.750 0.7071 0.02085 0.01098 -0.0861 0.5503 0.7316 3.000 0.7299 0.02113 0.01140 -0.0856 0.5465 0.7459 3.250 0.7526 0.02139 0.01180 -0.0850 0.5426 0.7626 3.500 0.7770 0.02154 0.01207 -0.0844 0.5394 0.7841 3.750 0.8021 0.02160 0.01224 -0.0839 0.5369 0.8121 4.000 0.8287 0.02161 0.01236 -0.0835 0.5349 0.8544 4.250 0.8590 0.02203 0.01307 -0.0848 0.5305 1.0000 4.500 0.8832 0.02248 0.01355 -0.0848 0.5268 1.0000 4.750 0.9101 0.02277 0.01383 -0.0850 0.5237 1.0000 5.000 0.9386 0.02299 0.01404 -0.0854 0.5213 1.0000 5.250 0.9614 0.02352 0.01463 -0.0851 0.5180 1.0000 5.500 0.9799 0.02425 0.01548 -0.0843 0.5136 1.0000 5.750 1.0038 0.02467 0.01596 -0.0840 0.5102 1.0000 6.000 1.0312 0.02491 0.01624 -0.0841 0.5074 1.0000 6.250 1.0607 0.02507 0.01641 -0.0845 0.5053 1.0000 6.500 1.0696 0.02623 0.01779 -0.0825 0.4993 1.0000 6.750 1.0910 0.02675 0.01841 -0.0819 0.4954 1.0000 7.000 1.1180 0.02698 0.01870 -0.0819 0.4925 1.0000 7.250 1.1483 0.02709 0.01885 -0.0823 0.4903 1.0000 7.500 1.1481 0.02864 0.02065 -0.0793 0.4834 1.0000 7.750 1.1691 0.02915 0.02127 -0.0787 0.4797 1.0000 8.000 1.1971 0.02934 0.02156 -0.0788 0.4771 1.0000 8.250 1.2045 0.03051 0.02291 -0.0766 0.4719 1.0000 8.500 1.2106 0.03167 0.02423 -0.0743 0.4664 1.0000 8.750 1.2370 0.03185 0.02452 -0.0742 0.4633 1.0000 9.000 1.2724 0.03159 0.02439 -0.0750 0.4610 1.0000 9.250 1.2320 0.03468 0.02766 -0.0677 0.4514 1.0000 9.500 1.2655 0.03434 0.02745 -0.0681 0.4484 1.0000 9.750 1.2096 0.03904 0.03224 -0.0614 0.4375 1.0000 10.000 1.2437 0.03833 0.03168 -0.0613 0.4345 1.0000 10.250 1.2816 0.03729 0.03079 -0.0615 0.4308 1.0000 10.750 1.1907 0.04885 0.04245 -0.0559 0.4057 1.0000 11.250 1.2080 0.05080 0.04461 -0.0540 0.3859 1.0000 11.500 1.2146 0.05152 0.04539 -0.0529 0.3685 1.0000 11.750 1.2286 0.05133 0.04520 -0.0518 0.3437 1.0000 12.000 1.2270 0.05365 0.04753 -0.0511 0.3229 1.0000 12.250 1.2339 0.05501 0.04886 -0.0503 0.3015 1.0000 12.500 1.2269 0.05830 0.05217 -0.0499 0.2792 1.0000 12.750 1.2274 0.06035 0.05401 -0.0490 0.2417 1.0000 13.000 1.2181 0.06376 0.05710 -0.0485 0.2018 1.0000 13.250 1.2033 0.06822 0.06133 -0.0485 0.1691 1.0000 13.500 1.1862 0.07329 0.06617 -0.0488 0.1393 1.0000 13.750 1.1701 0.07849 0.07119 -0.0494 0.1119 1.0000 14.000 1.1562 0.08360 0.07613 -0.0502 0.0884 1.0000 14.250 1.1448 0.08853 0.08094 -0.0510 0.0705 1.0000 14.500 1.1361 0.09321 0.08555 -0.0519 0.0573 1.0000 14.750 1.1293 0.09772 0.09002 -0.0528 0.0483 1.0000