XFOIL Version 6.94 Calculated polar for: MH 201 13.08% 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.4461 0.00853 0.00399 -0.1017 0.7769 0.7695 0.500 0.5009 0.00865 0.00405 -0.1012 0.7619 0.7788 1.000 0.5587 0.00876 0.00405 -0.1015 0.7431 0.7855 1.500 0.6108 0.00857 0.00391 -0.1007 0.7283 0.7950 2.000 0.6634 0.00866 0.00392 -0.0997 0.7047 0.8030 2.500 0.7155 0.00872 0.00404 -0.0987 0.6841 0.8114 3.000 0.7677 0.00885 0.00404 -0.0979 0.6497 0.8174 3.500 0.8177 0.00909 0.00415 -0.0966 0.6072 0.8234 4.000 0.8660 0.00948 0.00435 -0.0952 0.5552 0.8268 4.500 0.9137 0.00986 0.00455 -0.0940 0.4996 0.8327 5.000 0.9573 0.01039 0.00487 -0.0919 0.4395 0.8399 5.500 0.9990 0.01106 0.00539 -0.0894 0.3855 0.8473 6.000 1.0380 0.01190 0.00597 -0.0866 0.3268 0.8551 6.500 1.0791 0.01273 0.00661 -0.0843 0.2778 0.8615 7.000 1.1203 0.01358 0.00730 -0.0821 0.2372 0.8669 7.500 1.1574 0.01448 0.00804 -0.0793 0.1973 0.8730 8.000 1.1931 0.01530 0.00883 -0.0762 0.1690 0.8834 8.500 1.2275 0.01623 0.00976 -0.0729 0.1438 0.8939 9.000 1.2577 0.01747 0.01092 -0.0691 0.1189 0.9061 9.500 1.2851 0.01854 0.01199 -0.0650 0.1016 0.9261 10.000 1.3108 0.01965 0.01339 -0.0607 0.0881 1.0000 10.500 1.3451 0.02134 0.01505 -0.0591 0.0751 1.0000 11.000 1.3740 0.02320 0.01699 -0.0566 0.0634 1.0000 11.500 1.4028 0.02502 0.01886 -0.0543 0.0546 1.0000 12.000 1.4113 0.02843 0.02237 -0.0501 0.0440 1.0000 12.500 1.4412 0.03025 0.02435 -0.0485 0.0406 1.0000 13.000 1.4560 0.03330 0.02746 -0.0459 0.0341 1.0000 13.500 1.4362 0.03981 0.03427 -0.0415 0.0270 1.0000 14.000 1.4560 0.04296 0.03760 -0.0403 0.0260 1.0000 14.500 1.4674 0.04710 0.04202 -0.0394 0.0242 1.0000 15.000 1.4739 0.05200 0.04713 -0.0388 0.0218 1.0000 15.500 1.4757 0.05774 0.05299 -0.0391 0.0188 1.0000 16.000 1.4431 0.06830 0.06384 -0.0406 0.0154 1.0000 16.500 1.4055 0.08089 0.07689 -0.0438 0.0139 1.0000 17.000 1.4029 0.08907 0.08529 -0.0473 0.0135 1.0000 17.500 1.3933 0.09858 0.09506 -0.0517 0.0131 1.0000 18.000 1.3776 0.10933 0.10608 -0.0573 0.0125 1.0000 18.500 1.3582 0.12093 0.11794 -0.0640 0.0119 1.0000 19.000 1.3329 0.13353 0.13083 -0.0719 0.0115 1.0000 19.500 1.3014 0.14771 0.14531 -0.0815 0.0112 1.0000 20.000 1.2608 0.16587 0.16379 -0.0931 0.0113 1.0000