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 = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.250 -0.5066 0.09440 0.09245 -0.0229 1.0000 0.0178 -11.000 -0.4945 0.09329 0.09134 -0.0240 1.0000 0.0185 -10.500 -0.6665 0.04226 0.03944 -0.0646 0.9678 0.0108 -10.250 -0.6876 0.03938 0.03630 -0.0615 0.9498 0.0107 -10.000 -0.7036 0.03669 0.03335 -0.0576 0.9390 0.0106 -9.500 -0.7108 0.03124 0.02728 -0.0517 0.9248 0.0106 -9.250 -0.7041 0.02919 0.02493 -0.0493 0.9198 0.0107 -9.000 -0.6927 0.02740 0.02287 -0.0474 0.9158 0.0109 -8.750 -0.6773 0.02573 0.02096 -0.0459 0.9115 0.0110 -8.500 -0.6611 0.02440 0.01939 -0.0443 0.9076 0.0113 -8.250 -0.6484 0.02216 0.01687 -0.0421 0.9041 0.0114 -8.000 -0.6322 0.02003 0.01452 -0.0406 0.9007 0.0118 -7.750 -0.6129 0.01865 0.01301 -0.0394 0.8972 0.0123 -7.500 -0.5922 0.01769 0.01193 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