XFOIL Version 6.94 Calculated polar for: BL BAP 04 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.045 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.0048 0.04314 0.03507 -0.0734 0.9131 0.2273 -2.750 0.0263 0.04107 0.03286 -0.0745 0.9051 0.2178 -2.500 0.0612 0.03998 0.03128 -0.0757 0.8930 0.2060 -2.250 0.0803 0.03917 0.03045 -0.0740 0.8708 0.2025 -2.000 0.0741 0.03874 0.03015 -0.0683 0.7833 0.2011 -1.750 0.1795 0.03429 0.02500 -0.0814 0.7357 0.1955 -1.500 0.2930 0.03111 0.02073 -0.0967 0.6986 0.1939 -1.250 0.3542 0.03026 0.01926 -0.1027 0.6815 0.1958 -0.750 0.4472 0.02951 0.01790 -0.1095 0.6585 0.2100 -0.500 0.4906 0.02938 0.01763 -0.1126 0.6487 0.2269 -0.250 0.5310 0.02926 0.01756 -0.1151 0.6384 0.2528 0.000 0.5607 0.02682 0.01737 -0.1147 0.6291 1.0002 0.250 0.6026 0.02779 0.01747 -0.1165 0.6179 1.0002 0.500 0.6402 0.02886 0.01806 -0.1184 0.6073 1.0002 0.750 0.6759 0.03004 0.01892 -0.1201 0.5983 1.0002 1.000 0.7101 0.03147 0.02008 -0.1216 0.5899 1.0002 1.250 0.7417 0.03324 0.02163 -0.1228 0.5819 1.0002 1.500 0.7701 0.03542 0.02368 -0.1235 0.5735 1.0002 1.750 0.7949 0.03812 0.02632 -0.1237 0.5641 1.0002 2.000 0.8157 0.04179 0.02994 -0.1233 0.5525 1.0002 2.250 0.8295 0.04545 0.03372 -0.1218 0.5364 1.0002 2.500 0.8343 0.05057 0.03895 -0.1189 0.5107 1.0002 2.750 0.8446 0.05541 0.04380 -0.1170 0.4918 1.0002 3.000 0.8554 0.05784 0.04639 -0.1150 0.4770 1.0002 3.250 0.8692 0.06089 0.04950 -0.1136 0.4667 1.0002 3.500 0.8845 0.06496 0.05356 -0.1127 0.4576 1.0002 3.750 0.8960 0.06667 0.05541 -0.1109 0.4481 1.0002 4.000 0.9060 0.06879 0.05767 -0.1092 0.4408 1.0002 4.500 0.9266 0.07420 0.06327 -0.1061 0.4286 1.0002 4.750 0.9424 0.07859 0.06768 -0.1056 0.4234 1.0002 5.000 0.9412 0.08001 0.06931 -0.1028 0.4186 1.0002