XFOIL Version 6.96 Calculated polar for: WORTMANN FX 049-915 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.500 -0.6974 0.03660 0.03259 -0.0902 0.4968 0.0117 -12.250 -0.7269 0.03248 0.02819 -0.0854 0.4962 0.0118 -12.000 -0.7299 0.03010 0.02560 -0.0825 0.4948 0.0119 -11.750 -0.7277 0.02804 0.02334 -0.0799 0.4931 0.0120 -11.500 -0.7158 0.02680 0.02200 -0.0781 0.4923 0.0122 -11.250 -0.7039 0.02542 0.02047 -0.0762 0.4915 0.0123 -11.000 -0.6890 0.02430 0.01922 -0.0746 0.4905 0.0126 -10.750 -0.6719 0.02334 0.01814 -0.0732 0.4893 0.0128 -10.500 -0.6543 0.02237 0.01705 -0.0718 0.4882 0.0131 -10.250 -0.6371 0.02129 0.01580 -0.0703 0.4870 0.0134 -10.000 -0.6177 0.02043 0.01480 -0.0690 0.4858 0.0137 -9.750 -0.5975 0.01964 0.01387 -0.0678 0.4845 0.0139 -9.500 -0.5761 0.01897 0.01306 -0.0667 0.4832 0.0141 -9.250 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