XFOIL Version 6.96 Calculated polar for: FX 78-K-150/20 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 ------ -------- --------- --------- -------- -------- -------- -13.500 -0.1795 0.13562 0.12961 -0.0874 0.7940 0.0470 -13.250 -0.1732 0.13238 0.12639 -0.0890 0.7928 0.0460 -12.750 -0.1839 0.12063 0.11468 -0.0952 0.7908 0.0294 -12.500 -0.1753 0.11758 0.11162 -0.0959 0.7897 0.0288 -12.250 -0.1718 0.11380 0.10786 -0.0972 0.7886 0.0286 -12.000 -0.1673 0.11046 0.10452 -0.0984 0.7875 0.0281 -11.750 -0.1665 0.10649 0.10055 -0.1000 0.7863 0.0281 -11.500 -0.1682 0.10211 0.09620 -0.1019 0.7852 0.0284 -11.250 -0.1662 0.09875 0.09285 -0.1033 0.7841 0.0282 -11.000 -0.1694 0.09436 0.08851 -0.1052 0.7827 0.0284 -10.750 -0.1661 0.09148 0.08566 -0.1061 0.7811 0.0274 -10.500 -0.1856 0.08370 0.07801 -0.1105 0.7798 0.0293 -10.250 -0.1923 0.07895 0.07332 -0.1127 0.7783 0.0292 -10.000 -0.1940 0.07566 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0.05457 0.04449 -0.0214 0.0304 1.0000 11.250 0.9418 0.05633 0.04638 -0.0205 0.0281 1.0000 11.500 0.9494 0.05816 0.04829 -0.0197 0.0258 1.0000 11.750 0.9558 0.06006 0.05028 -0.0187 0.0245 1.0000 12.000 0.9621 0.06186 0.05211 -0.0173 0.0235 1.0000 12.250 0.9752 0.06304 0.05336 -0.0161 0.0227 1.0000 12.500 0.9919 0.06391 0.05431 -0.0149 0.0222 1.0000 12.750 1.0121 0.06455 0.05503 -0.0137 0.0214 1.0000 13.000 1.0361 0.06511 0.05570 -0.0125 0.0208 1.0000 13.250 1.0561 0.06619 0.05690 -0.0117 0.0197 1.0000 13.500 1.0742 0.06756 0.05845 -0.0110 0.0186 1.0000 13.750 1.0867 0.06934 0.06030 -0.0105 0.0175 1.0000 14.000 1.1071 0.07102 0.06216 -0.0097 0.0173 1.0000 14.250 1.1280 0.07349 0.06480 -0.0090 0.0168 1.0000 14.500 1.1361 0.07665 0.06822 -0.0082 0.0165 1.0000 14.750 1.1372 0.08008 0.07197 -0.0074 0.0164 1.0000 15.000 1.1375 0.08336 0.07549 -0.0069 0.0164 1.0000 15.250 1.1305 0.08737 0.07980 -0.0064 0.0163 1.0000 15.500 1.1216 0.09165 0.08438 -0.0061 0.0163 1.0000 15.750 1.1125 0.09595 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