XFOIL Version 6.96 Calculated polar for: FX 63-137 13.7% smoothed 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.750 -0.1616 0.11682 0.11309 -0.0676 0.9777 0.0308 -10.500 -0.1506 0.11288 0.10916 -0.0708 0.9725 0.0313 -10.250 -0.1531 0.10483 0.10110 -0.0762 0.9654 0.0238 -10.000 -0.1380 0.10248 0.09875 -0.0772 0.9583 0.0226 -9.500 -0.1207 0.09377 0.09005 -0.0833 0.9434 0.0213 -9.250 -0.1146 0.08750 0.08377 -0.0885 0.9377 0.0204 -9.000 -0.1048 0.08340 0.07967 -0.0919 0.9294 0.0207 -8.750 -0.0935 0.07797 0.07424 -0.0975 0.9238 0.0207 -8.250 -0.1454 0.03782 0.03326 -0.1486 0.8915 0.0197 -8.000 -0.1219 0.03140 0.02614 -0.1605 0.8804 0.0198 -7.750 -0.0851 0.02832 0.02271 -0.1668 0.8751 0.0201 -7.500 -0.0548 0.02623 0.02036 -0.1702 0.8674 0.0206 -7.250 -0.0197 0.02429 0.01810 -0.1738 0.8611 0.0211 -7.000 0.0160 0.02249 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