XFOIL Version 6.94 Calculated polar for: GD BAP 02 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.018 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.1939 0.06068 0.04762 -0.0354 0.9998 0.3876 -2.750 -0.1574 0.05871 0.04530 -0.0391 0.9998 0.3819 -2.500 -0.1215 0.05696 0.04324 -0.0422 0.9998 0.3790 -2.250 -0.0854 0.05550 0.04145 -0.0451 0.9998 0.3783 -2.000 -0.0498 0.05427 0.03990 -0.0476 0.9998 0.3794 -1.750 -0.0147 0.05324 0.03855 -0.0497 0.9998 0.3818 -1.500 0.0199 0.05241 0.03737 -0.0515 0.9998 0.3852 -1.250 0.0515 0.05150 0.03641 -0.0524 0.9998 0.3915 -1.000 0.0828 0.05080 0.03566 -0.0532 0.9998 0.4028 -0.750 0.1141 0.05019 0.03507 -0.0539 0.9998 0.4185 -0.500 0.1449 0.04960 0.03465 -0.0544 0.9998 0.4420 -0.250 0.1746 0.04882 0.03442 -0.0546 0.9998 0.4816 0.000 0.2012 0.04739 0.03441 -0.0537 0.9998 0.5871 0.250 0.2102 0.04587 0.03343 -0.0497 0.9998 1.0002 0.500 0.2423 0.04680 0.03345 -0.0501 0.9998 1.0002 0.750 0.2670 0.04787 0.03402 -0.0499 0.9998 1.0002 1.000 0.2825 0.04977 0.03589 -0.0500 0.9998 1.0002 1.250 0.2784 0.05800 0.04458 -0.0590 0.9791 1.0002 1.500 0.3690 0.06052 0.04630 -0.0751 0.9029 1.0002 1.750 0.4214 0.06194 0.04728 -0.0819 0.8626 1.0002 2.000 0.4548 0.06336 0.04842 -0.0851 0.8328 1.0002 2.250 0.4985 0.06452 0.04928 -0.0893 0.8090 1.0002 2.500 0.5295 0.06624 0.05079 -0.0918 0.7912 1.0002 2.750 0.5419 0.06899 0.05340 -0.0923 0.7792 1.0002 3.000 0.5670 0.07141 0.05566 -0.0944 0.7694 1.0002 3.250 0.5769 0.07447 0.05863 -0.0947 0.7613 1.0002 3.500 0.6061 0.07682 0.06084 -0.0971 0.7526 1.0002 3.750 0.6051 0.08044 0.06440 -0.0962 0.7476 1.0002 4.000 0.6114 0.08384 0.06773 -0.0963 0.7435 1.0002 4.250 0.6159 0.08747 0.07131 -0.0964 0.7426 1.0002 4.500 0.6164 0.09134 0.07513 -0.0963 0.7450 1.0002 4.750 0.6190 0.09510 0.07885 -0.0965 0.7476 1.0002 5.000 0.6243 0.09878 0.08249 -0.0968 0.7502 1.0002