XFOIL Version 6.94 Calculated polar for: NN7 MK20 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.4390 0.01501 0.00899 -0.0975 0.6872 0.6740 0.500 0.4943 0.01495 0.00894 -0.0978 0.6788 0.6793 1.000 0.5520 0.01496 0.00888 -0.0986 0.6710 0.6864 1.500 0.6111 0.01509 0.00887 -0.0998 0.6621 0.6922 2.000 0.6635 0.01491 0.00879 -0.0996 0.6541 0.6965 2.500 0.7180 0.01486 0.00881 -0.0998 0.6452 0.7001 3.000 0.7747 0.01482 0.00875 -0.1002 0.6365 0.7045 3.500 0.8303 0.01500 0.00893 -0.1006 0.6265 0.7093 4.000 0.8844 0.01499 0.00902 -0.1009 0.6166 0.7137 4.500 0.9419 0.01479 0.00881 -0.1014 0.6033 0.7175 5.000 0.9960 0.01491 0.00899 -0.1016 0.5899 0.7208 5.500 1.0487 0.01463 0.00878 -0.1014 0.5757 0.7246 6.000 1.1019 0.01474 0.00893 -0.1012 0.5622 0.7289 6.500 1.1503 0.01469 0.00909 -0.1001 0.5444 0.7340 7.000 1.1976 0.01473 0.00916 -0.0987 0.5196 0.7389 7.500 1.2441 0.01498 0.00941 -0.0975 0.4964 0.7436 8.000 1.2835 0.01540 0.00981 -0.0950 0.4637 0.7477 8.500 1.3191 0.01599 0.01044 -0.0921 0.4327 0.7520 9.000 1.3357 0.01692 0.01129 -0.0859 0.3830 0.7568 9.500 1.3375 0.01903 0.01313 -0.0788 0.3169 0.7624 10.000 1.3340 0.02204 0.01587 -0.0725 0.2586 0.7681 10.500 1.3171 0.02663 0.02004 -0.0665 0.1905 0.7732 11.000 1.3100 0.03116 0.02428 -0.0625 0.1379 0.7784 11.500 1.3122 0.03510 0.02815 -0.0595 0.1072 0.7850 12.000 1.3157 0.03923 0.03228 -0.0570 0.0861 0.7912 12.500 1.3195 0.04369 0.03670 -0.0550 0.0631 0.7972 13.000 1.3233 0.04838 0.04135 -0.0535 0.0432 0.8026 13.500 1.3330 0.05260 0.04571 -0.0524 0.0360 0.8096 14.000 1.3374 0.05765 0.05087 -0.0516 0.0268 0.8170 14.500 1.3037 0.06767 0.06092 -0.0504 0.0090 0.8231 15.500 1.2934 0.08209 0.07597 -0.0514 0.0080 0.8406 16.500 1.2740 0.09736 0.09203 -0.0534 0.0076 1.0000 17.000 1.2732 0.10462 0.09950 -0.0555 0.0078 1.0000 17.500 1.2621 0.11338 0.10854 -0.0576 0.0074 1.0000 18.000 1.2603 0.12086 0.11625 -0.0602 0.0075 1.0000 18.500 1.2514 0.12951 0.12521 -0.0633 0.0075 1.0000 19.000 1.2402 0.13887 0.13488 -0.0675 0.0074 1.0000 19.500 1.2259 0.14896 0.14530 -0.0730 0.0075 1.0000 20.000 1.2072 0.16055 0.15723 -0.0802 0.0077 1.0000 20.500 1.1768 0.17648 0.17352 -0.0899 0.0078 1.0000 21.000 1.1378 0.19738 0.19477 -0.1021 0.0080 1.0000 21.500 1.0324 0.25163 0.24929 -0.1252 0.0094 1.0000