XFOIL Version 6.96 Calculated polar for: FX 77-W-121 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 ------ -------- --------- --------- -------- -------- -------- -9.000 -0.2750 0.09274 0.08877 -0.0326 0.5129 0.0178 -8.750 -0.2713 0.08936 0.08538 -0.0338 0.5108 0.0178 -8.500 -0.2699 0.08594 0.08196 -0.0360 0.5095 0.0178 -8.250 -0.2691 0.08239 0.07843 -0.0379 0.5076 0.0179 -8.000 -0.2709 0.07876 0.07485 -0.0398 0.5061 0.0178 -7.750 -0.2866 0.07365 0.06979 -0.0403 0.5052 0.0184 -7.500 -0.2893 0.07006 0.06619 -0.0420 0.5039 0.0183 -7.250 -0.2821 0.06847 0.06460 -0.0408 0.5021 0.0191 -7.000 -0.2793 0.06488 0.06098 -0.0424 0.5007 0.0192 -6.750 -0.2735 0.06160 0.05765 -0.0436 0.4991 0.0194 -6.500 -0.2663 0.05833 0.05431 -0.0444 0.4978 0.0198 -6.250 -0.2576 0.05495 0.05085 -0.0450 0.4968 0.0210 -6.000 -0.2475 0.05132 0.04709 -0.0455 0.4955 0.0215 -5.750 -0.2359 0.04769 0.04329 -0.0455 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1.2163 0.06871 0.06286 -0.0198 0.0094 1.0000 14.000 1.2100 0.07262 0.06686 -0.0203 0.0087 1.0000 14.250 1.2085 0.07591 0.07023 -0.0207 0.0086 1.0000 14.500 1.2072 0.07929 0.07369 -0.0212 0.0080 1.0000 14.750 1.2084 0.08228 0.07677 -0.0217 0.0081 1.0000 15.000 1.2037 0.08609 0.08065 -0.0222 0.0081 1.0000 15.250 1.2017 0.08958 0.08422 -0.0227 0.0079 1.0000