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 = 0.018 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.1936 0.05863 0.04748 -0.0329 0.9998 0.3852 -2.750 -0.1571 0.05642 0.04507 -0.0362 0.9998 0.3812 -2.500 -0.1187 0.05456 0.04292 -0.0398 0.9998 0.3791 -2.250 -0.0803 0.05300 0.04109 -0.0431 0.9998 0.3793 -2.000 -0.0423 0.05171 0.03953 -0.0462 0.9998 0.3810 -1.750 -0.0052 0.05068 0.03824 -0.0489 0.9998 0.3837 -1.500 0.0294 0.04981 0.03728 -0.0510 0.9998 0.3880 -1.250 0.0602 0.04922 0.03677 -0.0525 0.9998 0.3960 -1.000 0.0871 0.04932 0.03695 -0.0541 0.9998 0.4071 -0.750 0.1056 0.05060 0.03846 -0.0561 0.9964 0.4181 -0.500 0.1968 0.04962 0.03787 -0.0706 0.9467 0.4723 -0.250 0.2403 0.04815 0.03759 -0.0750 0.9069 0.5723 0.000 0.2679 0.04726 0.03697 -0.0761 0.8722 1.0002 0.250 0.3066 0.04878 0.03725 -0.0792 0.8507 1.0002 0.500 0.3392 0.05042 0.03802 -0.0816 0.8362 1.0002 0.750 0.3749 0.05195 0.03885 -0.0846 0.8241 1.0002 1.000 0.3971 0.05396 0.04044 -0.0860 0.8139 1.0002 1.250 0.4268 0.05575 0.04183 -0.0885 0.8050 1.0002 1.500 0.4445 0.05816 0.04396 -0.0896 0.7988 1.0002 1.750 0.4638 0.06074 0.04629 -0.0911 0.7956 1.0002 2.000 0.4732 0.06395 0.04931 -0.0917 0.7966 1.0002 2.250 0.4783 0.06739 0.05260 -0.0919 0.7997 1.0002 2.500 0.4857 0.07078 0.05584 -0.0924 0.8034 1.0002 2.750 0.4968 0.07407 0.05898 -0.0933 0.8068 1.0002 3.000 0.4885 0.07770 0.06255 -0.0918 0.8137 1.0002 3.250 0.4895 0.08113 0.06587 -0.0914 0.8206 1.0002 3.500 0.4866 0.08460 0.06926 -0.0906 0.8304 1.0002 3.750 0.4927 0.08835 0.07290 -0.0912 0.8427 1.0002 4.000 0.4687 0.09167 0.07622 -0.0875 0.8661 1.0002 4.250 0.4588 0.09518 0.07966 -0.0857 0.8918 1.0002 5.000 0.3821 0.10038 0.08472 -0.0679 0.9998 1.0002