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 = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.500 0.5452 0.00585 0.00169 -0.1069 0.7708 1.0000 1.000 0.5998 0.00613 0.00168 -0.1062 0.7235 1.0000 1.500 0.6539 0.00649 0.00174 -0.1055 0.6709 1.0000 2.000 0.7076 0.00693 0.00187 -0.1047 0.6121 1.0000 2.500 0.7606 0.00745 0.00207 -0.1040 0.5446 1.0000 3.000 0.8130 0.00808 0.00237 -0.1033 0.4719 1.0000 3.500 0.8655 0.00874 0.00273 -0.1026 0.4126 1.0000 4.000 0.9183 0.00936 0.00317 -0.1020 0.3715 1.0000 4.500 0.9714 0.00992 0.00364 -0.1015 0.3402 1.0000 5.000 1.0242 0.01049 0.00414 -0.1009 0.3139 1.0000 5.500 1.0768 0.01105 0.00469 -0.1003 0.2893 1.0000 6.000 1.1288 0.01164 0.00520 -0.0997 0.2504 1.0000 6.500 1.1800 0.01230 0.00580 -0.0989 0.2158 1.0000 7.000 1.2297 0.01314 0.00655 -0.0980 0.1738 1.0000 7.500 1.2718 0.01501 0.00789 -0.0962 0.0790 1.0000 8.000 1.3080 0.01775 0.01030 -0.0933 0.0252 1.0000 8.500 1.3482 0.01965 0.01237 -0.0908 0.0194 1.0000 9.000 1.3844 0.02179 0.01474 -0.0878 0.0164 1.0000 9.500 1.4095 0.02479 0.01791 -0.0835 0.0139 1.0000 10.000 1.4386 0.02709 0.02047 -0.0796 0.0125 1.0000 10.500 1.4576 0.02989 0.02347 -0.0746 0.0114 1.0000 11.000 1.4580 0.03424 0.02801 -0.0677 0.0106 1.0000 11.500 1.4660 0.03784 0.03198 -0.0625 0.0099 1.0000 12.000 1.4687 0.04229 0.03678 -0.0582 0.0093 1.0000 12.500 1.4645 0.04796 0.04282 -0.0548 0.0090 1.0000 13.000 1.4541 0.05483 0.05007 -0.0529 0.0088 1.0000 13.500 1.4378 0.06309 0.05869 -0.0530 0.0086 1.0000 14.000 1.4128 0.07350 0.06951 -0.0555 0.0086 1.0000 14.500 1.3804 0.08628 0.08270 -0.0606 0.0086 1.0000 15.000 1.3398 0.10229 0.09915 -0.0690 0.0087 1.0000 15.500 1.2944 0.12125 0.11852 -0.0803 0.0090 1.0000 16.000 1.2529 0.14134 0.13892 -0.0931 0.0093 1.0000 16.500 1.2125 0.16378 0.16162 -0.1080 0.0097 1.0000 17.000 1.1727 0.18930 0.18727 -0.1242 0.0103 1.0000