XFOIL Version 6.94 Calculated polar for: BE50 (smoothed) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.4926 0.00684 0.00252 -0.1094 0.8603 1.0000 0.500 0.5470 0.00692 0.00233 -0.1083 0.8241 1.0000 1.000 0.6010 0.00709 0.00224 -0.1071 0.7821 1.0000 1.500 0.6547 0.00737 0.00224 -0.1060 0.7336 1.0000 2.000 0.7078 0.00774 0.00232 -0.1050 0.6780 1.0000 2.500 0.7601 0.00823 0.00250 -0.1039 0.6142 1.0000 3.000 0.8115 0.00886 0.00276 -0.1027 0.5409 1.0000 3.500 0.8624 0.00960 0.00317 -0.1017 0.4673 1.0000 4.000 0.9136 0.01038 0.00366 -0.1008 0.4132 1.0000 4.500 0.9654 0.01110 0.00422 -0.1000 0.3747 1.0000 5.000 1.0171 0.01181 0.00488 -0.0993 0.3441 1.0000 5.500 1.0689 0.01250 0.00555 -0.0985 0.3170 1.0000 6.000 1.1202 0.01316 0.00625 -0.0977 0.2885 1.0000 6.500 1.1700 0.01385 0.00686 -0.0967 0.2488 1.0000 7.000 1.2199 0.01456 0.00758 -0.0958 0.2082 1.0000 7.500 1.2665 0.01570 0.00858 -0.0945 0.1481 1.0000 8.000 1.2962 0.01929 0.01140 -0.0909 0.0355 1.0000 9.000 1.3565 0.02512 0.01771 -0.0830 0.0214 1.0000 9.500 1.3840 0.02794 0.02081 -0.0789 0.0188 1.0000 10.000 1.4063 0.03122 0.02437 -0.0742 0.0169 1.0000 10.500 1.4207 0.03486 0.02828 -0.0687 0.0156 1.0000 11.000 1.4282 0.03956 0.03327 -0.0631 0.0146 1.0000 11.500 1.4209 0.04757 0.04180 -0.0574 0.0137 1.0000 12.000 1.4060 0.05343 0.04816 -0.0529 0.0132 1.0000 12.500 1.3901 0.06009 0.05530 -0.0508 0.0129 1.0000 13.000 1.3633 0.06957 0.06524 -0.0514 0.0128 1.0000 13.500 1.3300 0.08133 0.07741 -0.0552 0.0129 1.0000 14.000 1.2920 0.09549 0.09196 -0.0622 0.0130 1.0000 14.500 1.2504 0.11230 0.10908 -0.0719 0.0132 1.0000 16.500 0.8191 0.16479 0.16246 -0.0816 0.0210 1.0000