XFOIL Version 6.96 Calculated polar for: WORTMANN FX 75-193 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 -0.4895 0.10669 0.10320 -0.1018 0.7659 0.0050 -17.500 -0.5173 0.09660 0.09298 -0.1075 0.7658 0.0051 -17.250 -0.5665 0.08313 0.07926 -0.1153 0.7657 0.0048 -17.000 -0.5677 0.07799 0.07405 -0.1194 0.7656 0.0049 -16.750 -0.5801 0.07125 0.06718 -0.1243 0.7655 0.0050 -16.500 -0.5980 0.06410 0.05984 -0.1294 0.7653 0.0049 -16.250 -0.5967 0.06000 0.05565 -0.1329 0.7651 0.0050 -16.000 -0.5982 0.05572 0.05126 -0.1363 0.7649 0.0050 -15.750 -0.6012 0.05149 0.04690 -0.1394 0.7647 0.0050 -15.500 -0.5919 0.04893 0.04427 -0.1418 0.7645 0.0051 -15.250 -0.5903 0.04564 0.04085 -0.1441 0.7642 0.0051 -15.000 -0.5865 0.04274 0.03784 -0.1461 0.7639 0.0051 -14.750 -0.5788 0.04041 0.03542 -0.1478 0.7636 0.0051 -14.500 -0.5686 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