XFOIL Version 6.94 Calculated polar for: BL BAP 02 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 -0.1898 0.05740 0.04716 -0.0360 0.9998 0.3477 -2.750 -0.1472 0.05522 0.04456 -0.0412 0.9998 0.3371 -2.500 -0.1059 0.05366 0.04251 -0.0453 0.9998 0.3298 -2.250 -0.0696 0.05208 0.04070 -0.0477 0.9998 0.3261 -2.000 -0.0331 0.05080 0.03916 -0.0500 0.9998 0.3235 -1.750 0.0027 0.04978 0.03790 -0.0521 0.9998 0.3236 -1.500 0.0372 0.04901 0.03693 -0.0538 0.9998 0.3263 -1.250 0.0700 0.04854 0.03629 -0.0553 0.9998 0.3304 -1.000 0.0981 0.04829 0.03616 -0.0565 0.9998 0.3360 -0.750 0.2045 0.04626 0.03399 -0.0723 0.9483 0.3580 -0.500 0.2568 0.04413 0.03219 -0.0774 0.8866 0.3862 -0.250 0.2856 0.04318 0.03172 -0.0787 0.8266 0.4222 0.000 0.3154 0.04066 0.03122 -0.0783 0.7938 0.6582 0.250 0.3720 0.03955 0.02879 -0.0816 0.7663 1.0002 0.500 0.4335 0.03878 0.02688 -0.0857 0.7472 1.0002 0.750 0.5002 0.03784 0.02509 -0.0914 0.7294 1.0002 1.000 0.5677 0.03749 0.02404 -0.0982 0.7140 1.0002 1.250 0.6112 0.03831 0.02449 -0.1019 0.7044 1.0002 1.500 0.6545 0.03920 0.02508 -0.1057 0.6969 1.0002 1.750 0.7017 0.04000 0.02554 -0.1099 0.6902 1.0002 2.000 0.7258 0.04181 0.02732 -0.1109 0.6849 1.0002 2.250 0.7495 0.04374 0.02920 -0.1119 0.6798 1.0002 2.500 0.7720 0.04585 0.03128 -0.1129 0.6759 1.0002 2.750 0.7836 0.04879 0.03426 -0.1129 0.6750 1.0002 3.000 0.7692 0.05372 0.03931 -0.1105 0.6781 1.0002 3.250 0.7421 0.05991 0.04558 -0.1076 0.6837 1.0002 3.500 0.7316 0.06533 0.05098 -0.1067 0.6885 1.0002 4.000 0.6681 0.07916 0.06481 -0.1027 0.7093 1.0002 4.250 0.6380 0.08512 0.07077 -0.1006 0.7235 1.0002 4.500 0.6476 0.08936 0.07496 -0.1022 0.7332 1.0002 4.750 0.5998 0.09521 0.08086 -0.0983 0.7620 1.0002 5.000 0.5863 0.10006 0.08570 -0.0978 0.7885 1.0002