XFOIL Version 6.94 Calculated polar for: Rhode St. Genese 36 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 0.6341 0.01704 0.00945 -0.0671 0.2985 0.1607 0.500 0.6692 0.01788 0.01036 -0.0639 0.2987 0.1721 1.000 0.6948 0.01888 0.01156 -0.0593 0.2984 0.1884 2.000 0.8422 0.02199 0.01703 -0.0714 0.2965 0.9995 2.500 0.8558 0.02336 0.01844 -0.0653 0.2971 1.0000 3.000 0.8734 0.02450 0.01961 -0.0598 0.2982 1.0000 3.500 0.8731 0.02680 0.02201 -0.0526 0.2980 1.0000 4.000 0.8478 0.03043 0.02581 -0.0433 0.2973 1.0000 4.500 0.8229 0.03511 0.03065 -0.0359 0.2969 1.0000 5.000 0.7938 0.04048 0.03616 -0.0298 0.2973 1.0000 5.500 0.7825 0.04563 0.04140 -0.0264 0.2979 1.0000 6.000 0.7707 0.05144 0.04727 -0.0242 0.2988 1.0000 6.500 0.7620 0.05817 0.05406 -0.0229 0.2991 1.0000 7.000 1.1703 0.02348 0.01795 -0.0412 0.2863 1.0000 7.500 1.2041 0.02384 0.01829 -0.0391 0.2845 1.0000 8.000 1.2120 0.02557 0.02009 -0.0346 0.2829 1.0000 8.500 1.2434 0.02624 0.02074 -0.0327 0.2803 1.0000 9.000 1.3010 0.02463 0.01889 -0.0332 0.2620 1.0000 9.500 1.3310 0.02539 0.01928 -0.0312 0.2305 1.0000 10.000 1.3388 0.02767 0.02111 -0.0276 0.1854 1.0000 10.500 1.2866 0.03461 0.02764 -0.0212 0.1449 1.0000 11.000 1.2810 0.03896 0.03190 -0.0185 0.1226 1.0000 11.500 1.2272 0.04872 0.04195 -0.0159 0.1172 1.0000 12.000 1.2409 0.05180 0.04500 -0.0148 0.0935 1.0000 12.500 1.2374 0.05667 0.04976 -0.0134 0.0701 1.0000 13.000 1.2326 0.06210 0.05514 -0.0129 0.0643 1.0000 13.500 1.1972 0.07162 0.06482 -0.0136 0.0603 1.0000 14.500 1.1050 0.09502 0.08869 -0.0174 0.0545 1.0000 15.000 1.1105 0.09965 0.09340 -0.0179 0.0508 1.0000 15.500 1.1135 0.10461 0.09847 -0.0185 0.0490 1.0000