XFOIL Version 6.96 Calculated polar for: FX 84-W-140 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.000 -0.1834 0.10524 0.10275 -0.0647 0.8788 0.0298 -11.750 -0.4783 0.04892 0.04617 -0.1075 0.9228 0.0197 -11.500 -0.5104 0.04257 0.03958 -0.1117 0.9050 0.0194 -11.250 -0.5407 0.03835 0.03509 -0.1120 0.8903 0.0194 -11.000 -0.5667 0.03546 0.03191 -0.1091 0.8784 0.0195 -10.750 -0.5809 0.03267 0.02878 -0.1065 0.8692 0.0196 -10.500 -0.5828 0.03020 0.02594 -0.1046 0.8618 0.0198 -10.250 -0.5795 0.02777 0.02315 -0.1029 0.8550 0.0200 -10.000 -0.5713 0.02540 0.02053 -0.1016 0.8495 0.0205 -9.750 -0.5530 0.02434 0.01939 -0.1010 0.8437 0.0210 -9.500 -0.5332 0.02349 0.01841 -0.1004 0.8385 0.0215 -9.250 -0.5133 0.02255 0.01729 -0.0997 0.8338 0.0221 -9.000 -0.4925 0.02151 0.01609 -0.0991 0.8283 0.0229 -8.750 -0.4706 0.02063 0.01499 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