XFOIL Version 6.96 Calculated polar for: FX 68-H-120 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.750 -0.5009 0.08700 0.08252 -0.0307 1.0000 0.0215 -10.500 -0.5285 0.07630 0.07191 -0.0373 1.0000 0.0208 -10.250 -0.5760 0.06010 0.05559 -0.0518 1.0000 0.0198 -10.000 -0.6069 0.05278 0.04804 -0.0580 1.0000 0.0193 -9.750 -0.6290 0.04911 0.04418 -0.0573 1.0000 0.0192 -9.500 -0.6490 0.04659 0.04148 -0.0540 1.0000 0.0192 -9.250 -0.6692 0.04480 0.03951 -0.0491 1.0000 0.0192 -9.000 -0.6769 0.04222 0.03664 -0.0463 0.9960 0.0193 -8.750 -0.6664 0.03894 0.03294 -0.0466 0.9885 0.0198 -8.500 -0.6494 0.03598 0.02956 -0.0472 0.9832 0.0204 -8.250 -0.6317 0.03368 0.02689 -0.0470 0.9775 0.0213 -8.000 -0.6084 0.03173 0.02455 -0.0475 0.9733 0.0231 -7.750 -0.5864 0.02988 0.02235 -0.0475 0.9693 0.0245 -7.500 -0.5677 0.02814 0.02047 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