XFOIL Version 6.94 Calculated polar for: FX 78-K-140/20 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.3833 0.01238 0.00790 -0.0700 0.7024 0.9521 0.500 0.5005 0.01289 0.00826 -0.0825 0.7006 0.9683 1.000 0.5759 0.01287 0.00817 -0.0871 0.6985 0.9767 1.500 0.6510 0.01263 0.00783 -0.0917 0.6966 0.9803 2.000 0.7145 0.01292 0.00820 -0.0946 0.6906 0.9868 2.500 0.7832 0.01262 0.00788 -0.0979 0.6876 0.9914 3.000 0.8536 0.01234 0.00760 -0.1016 0.6852 0.9952 3.500 0.9201 0.01241 0.00780 -0.1052 0.6790 0.9999 4.000 0.9712 0.01203 0.00745 -0.1047 0.6757 1.0000 4.500 1.0146 0.01172 0.00724 -0.1027 0.6675 1.0000 5.000 1.0611 0.01127 0.00687 -0.1012 0.6595 1.0000 5.500 1.1074 0.01062 0.00631 -0.0994 0.6474 1.0000 6.000 1.1509 0.01011 0.00590 -0.0970 0.6306 1.0000 6.500 1.1835 0.00995 0.00577 -0.0928 0.5879 1.0000 7.000 1.1695 0.01153 0.00675 -0.0805 0.4723 1.0000 7.500 1.0922 0.01538 0.01004 -0.0601 0.3821 1.0000 8.000 1.0551 0.01980 0.01390 -0.0491 0.2823 1.0000 8.500 1.0010 0.02608 0.01902 -0.0378 0.0943 1.0000 9.000 0.9913 0.03030 0.02277 -0.0320 0.0138 1.0000 9.500 1.0132 0.03265 0.02527 -0.0295 0.0118 1.0000 10.000 1.0337 0.03520 0.02796 -0.0270 0.0112 1.0000 10.500 1.0417 0.03889 0.03183 -0.0237 0.0085 1.0000 11.000 1.0444 0.04317 0.03628 -0.0200 0.0094 1.0000 11.500 1.0589 0.04643 0.03967 -0.0171 0.0095 1.0000 12.000 1.0822 0.04914 0.04246 -0.0161 0.0073 1.0000 12.500 1.1026 0.05178 0.04522 -0.0117 0.0064 1.0000 13.000 1.1488 0.05344 0.04730 -0.0081 0.0078 1.0000