XFOIL Version 6.94 Calculated polar for: MH 38 9.68% 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 ------- -------- --------- --------- -------- ------- ------- 0.000 0.4333 0.00679 0.00229 -0.0941 0.6903 1.0000 0.500 0.4897 0.00684 0.00226 -0.0942 0.6839 1.0000 1.000 0.5458 0.00691 0.00225 -0.0942 0.6728 1.0000 1.500 0.6018 0.00704 0.00227 -0.0942 0.6609 1.0000 2.000 0.6575 0.00735 0.00246 -0.0942 0.6436 1.0000 2.500 0.7136 0.00739 0.00256 -0.0942 0.6354 1.0000 3.000 0.7693 0.00748 0.00265 -0.0941 0.6213 1.0000 3.500 0.8241 0.00773 0.00283 -0.0938 0.6019 1.0000 4.000 0.8796 0.00788 0.00307 -0.0937 0.5881 1.0000 4.500 0.9342 0.00804 0.00327 -0.0935 0.5674 1.0000 5.000 0.9879 0.00831 0.00357 -0.0930 0.5420 1.0000 5.500 1.0393 0.00868 0.00386 -0.0922 0.4987 1.0000 6.000 1.0885 0.00928 0.00436 -0.0910 0.4359 1.0000 6.500 1.1298 0.01060 0.00520 -0.0890 0.3303 1.0000 7.000 1.1606 0.01297 0.00670 -0.0858 0.1771 1.0000 7.500 1.1806 0.01623 0.00897 -0.0814 0.0349 1.0000 8.500 1.2289 0.02098 0.01402 -0.0720 0.0082 1.0000 9.000 1.2293 0.02450 0.01786 -0.0646 0.0069 1.0000 9.500 1.2360 0.02845 0.02211 -0.0592 0.0067 1.0000 10.000 1.2506 0.03349 0.02750 -0.0547 0.0064 1.0000 10.500 1.2682 0.04058 0.03511 -0.0510 0.0060 1.0000 11.000 1.2652 0.04818 0.04337 -0.0471 0.0059 1.0000 11.500 1.2559 0.05437 0.04994 -0.0441 0.0059 1.0000 12.000 1.2385 0.06178 0.05774 -0.0425 0.0060 1.0000 12.500 1.2221 0.06905 0.06533 -0.0423 0.0061 1.0000 13.000 1.2007 0.07769 0.07428 -0.0440 0.0062 1.0000 13.500 1.1818 0.08701 0.08390 -0.0474 0.0065 1.0000 14.000 1.1571 0.09877 0.09597 -0.0532 0.0066 1.0000 14.500 1.1266 0.11345 0.11095 -0.0620 0.0068 1.0000 15.000 1.0946 0.13120 0.12901 -0.0738 0.0072 1.0000