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 = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -17.750 -0.8828 0.09441 0.09221 -0.0464 1.0000 0.0049 -17.500 -0.9460 0.07864 0.07619 -0.0555 1.0000 0.0048 -17.250 -0.9922 0.06686 0.06417 -0.0628 1.0000 0.0047 -17.000 -1.0097 0.06049 0.05766 -0.0666 1.0000 0.0048 -16.750 -1.0298 0.05413 0.05114 -0.0703 1.0000 0.0047 -16.500 -1.0437 0.04909 0.04595 -0.0728 1.0000 0.0047 -16.250 -1.0542 0.04485 0.04157 -0.0746 1.0000 0.0048 -16.000 -1.0551 0.04200 0.03865 -0.0755 1.0000 0.0049 -15.750 -1.0623 0.03866 0.03517 -0.0762 1.0000 0.0050 -15.500 -1.0650 0.03599 0.03239 -0.0764 1.0000 0.0050 -15.250 -1.0656 0.03372 0.03001 -0.0761 1.0000 0.0051 -15.000 -1.0634 0.03184 0.02802 -0.0755 1.0000 0.0052 -14.750 -1.0607 0.03012 0.02620 -0.0746 1.0000 0.0053 -14.500 -1.0574 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