XFOIL Version 6.96 Calculated polar for: MB253515 15.0% smoothed 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.250 -0.7670 0.07431 0.07166 -0.0596 1.0000 0.0079 -15.000 -0.8087 0.06289 0.06001 -0.0671 1.0000 0.0078 -14.750 -0.8373 0.05499 0.05189 -0.0720 1.0000 0.0078 -14.500 -0.8591 0.04903 0.04573 -0.0749 1.0000 0.0078 -14.250 -0.8725 0.04473 0.04124 -0.0764 1.0000 0.0078 -14.000 -0.8843 0.04101 0.03733 -0.0769 1.0000 0.0079 -13.750 -0.8913 0.03807 0.03421 -0.0766 1.0000 0.0081 -13.500 -0.9006 0.03519 0.03112 -0.0756 1.0000 0.0082 -13.250 -0.9025 0.03317 0.02893 -0.0742 1.0000 0.0083 -13.000 -0.9040 0.03133 0.02694 -0.0724 1.0000 0.0084 -12.750 -0.9079 0.02956 0.02505 -0.0700 1.0000 0.0087 -12.500 -0.9062 0.02836 0.02376 -0.0675 1.0000 0.0088 -12.250 -0.9040 0.02738 0.02271 -0.0647 1.0000 0.0091 -12.000 -0.8998 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18.000 1.1065 0.10265 0.09802 0.0032 0.0052 1.0000 18.250 1.1046 0.10636 0.10183 0.0021 0.0051 1.0000 18.500 1.1037 0.11003 0.10559 0.0007 0.0050 1.0000 18.750 1.1012 0.11387 0.10952 -0.0006 0.0050 1.0000 19.000 1.0983 0.11786 0.11361 -0.0021 0.0049 1.0000