XFOIL Version 6.94 Calculated polar for: BL BAP 05 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.022 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.1857 0.05612 0.04610 -0.0354 0.9998 0.3462 -2.750 -0.1415 0.05401 0.04351 -0.0410 0.9998 0.3351 -2.500 -0.1019 0.05240 0.04149 -0.0445 0.9998 0.3291 -2.250 -0.0652 0.05085 0.03973 -0.0471 0.9998 0.3256 -2.000 -0.0285 0.04961 0.03826 -0.0495 0.9998 0.3235 -1.750 0.0070 0.04868 0.03711 -0.0517 0.9998 0.3243 -1.500 0.0403 0.04810 0.03638 -0.0536 0.9998 0.3273 -1.250 0.1022 0.04718 0.03532 -0.0616 0.9817 0.3346 -1.000 0.1891 0.04492 0.03300 -0.0735 0.9301 0.3509 -0.750 0.2239 0.04358 0.03178 -0.0757 0.8683 0.3655 -0.500 0.2548 0.04322 0.03153 -0.0776 0.8190 0.3883 -0.250 0.3016 0.04183 0.03076 -0.0814 0.7925 0.4469 0.000 0.3411 0.03861 0.02890 -0.0815 0.7738 1.0002 0.250 0.4027 0.03828 0.02709 -0.0856 0.7573 1.0002 0.500 0.4636 0.03779 0.02565 -0.0904 0.7424 1.0002 0.750 0.5301 0.03748 0.02459 -0.0971 0.7303 1.0002 1.000 0.5722 0.03844 0.02518 -0.1009 0.7239 1.0002 1.250 0.6113 0.03961 0.02609 -0.1044 0.7197 1.0002 1.500 0.6478 0.04098 0.02724 -0.1075 0.7165 1.0002 1.750 0.6859 0.04233 0.02838 -0.1108 0.7130 1.0002 2.000 0.7030 0.04487 0.03088 -0.1115 0.7116 1.0002 2.250 0.7121 0.04810 0.03411 -0.1116 0.7119 1.0002 2.500 0.6370 0.05746 0.04367 -0.1039 0.7239 1.0002 2.750 0.6331 0.06247 0.04861 -0.1041 0.7317 1.0002 3.000 0.5911 0.06966 0.05582 -0.1008 0.7479 1.0002 3.250 0.5681 0.07521 0.06135 -0.0990 0.7636 1.0002 3.500 0.5503 0.08015 0.06626 -0.0975 0.7806 1.0002 3.750 0.5317 0.08475 0.07083 -0.0956 0.8004 1.0002 4.000 0.5199 0.08909 0.07514 -0.0945 0.8224 1.0002 4.250 0.4939 0.09340 0.07945 -0.0914 0.8566 1.0002 4.750 0.3727 0.09708 0.08317 -0.0693 0.9998 1.0002 5.000 0.3858 0.09973 0.08571 -0.0701 0.9998 1.0002