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 = 0.026 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.1705 0.05422 0.04468 -0.0399 0.9998 0.3105 -2.750 -0.1299 0.05247 0.04253 -0.0439 0.9998 0.3026 -2.500 -0.0945 0.05062 0.04052 -0.0463 0.9998 0.2982 -2.250 -0.0581 0.04909 0.03879 -0.0487 0.9998 0.2935 -2.000 -0.0209 0.04791 0.03734 -0.0512 0.9998 0.2890 -1.750 0.0635 0.04598 0.03486 -0.0630 0.9744 0.2860 -1.500 0.1444 0.04336 0.03192 -0.0731 0.9304 0.2895 -1.250 0.1762 0.04164 0.03018 -0.0737 0.8771 0.2952 -1.000 0.1833 0.04136 0.02997 -0.0708 0.7921 0.2992 -0.750 0.2537 0.03896 0.02738 -0.0773 0.7521 0.3154 -0.500 0.3392 0.03589 0.02411 -0.0859 0.7233 0.3528 -0.250 0.4014 0.03149 0.02190 -0.0902 0.7016 0.8407 0.000 0.4692 0.03140 0.01995 -0.0956 0.6848 1.0002 0.250 0.5192 0.03194 0.01959 -0.0995 0.6759 1.0002 0.500 0.5662 0.03258 0.01965 -0.1035 0.6709 1.0002 0.750 0.6109 0.03333 0.01999 -0.1073 0.6678 1.0002 1.000 0.6492 0.03420 0.02065 -0.1102 0.6654 1.0002 1.250 0.6850 0.03519 0.02151 -0.1127 0.6631 1.0002 1.500 0.7186 0.03631 0.02256 -0.1149 0.6611 1.0002 1.750 0.7502 0.03759 0.02383 -0.1169 0.6607 1.0002 2.000 0.7801 0.03906 0.02534 -0.1189 0.6631 1.0002 2.250 0.8085 0.04076 0.02709 -0.1208 0.6662 1.0002 2.500 0.8228 0.04319 0.02971 -0.1211 0.6703 1.0002 2.750 0.8050 0.04780 0.03463 -0.1181 0.6790 1.0002 3.000 0.7944 0.05281 0.03976 -0.1167 0.6877 1.0002 3.500 0.6059 0.07603 0.06325 -0.1028 0.7499 1.0002 3.750 0.5570 0.08284 0.07010 -0.0991 0.7840 1.0002 4.000 0.5269 0.08866 0.07593 -0.0970 0.8244 1.0002 4.500 0.3626 0.09402 0.08146 -0.0702 0.9998 1.0002 4.750 0.3759 0.09666 0.08398 -0.0710 0.9998 1.0002 5.000 0.3892 0.09932 0.08655 -0.0719 0.9998 1.0002