XFOIL Version 6.96 Calculated polar for: FX 78-K-140/20 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.250 -0.1843 0.09416 0.08972 -0.0801 0.7545 0.0135 -10.000 -0.1853 0.09012 0.08571 -0.0817 0.7535 0.0132 -9.750 -0.1884 0.08580 0.08143 -0.0835 0.7525 0.0133 -9.500 -0.1920 0.08160 0.07725 -0.0853 0.7516 0.0131 -9.250 -0.1949 0.07779 0.07347 -0.0870 0.7502 0.0126 -9.000 -0.2033 0.07315 0.06892 -0.0894 0.7483 0.0124 -8.750 -0.2180 0.06775 0.06361 -0.0931 0.7464 0.0120 -8.500 -0.2336 0.06337 0.05925 -0.0948 0.7445 0.0121 -8.250 -0.2589 0.05855 0.05437 -0.0935 0.7428 0.0116 -8.000 -0.2734 0.05388 0.04958 -0.0923 0.7413 0.0114 -7.750 -0.2919 0.04745 0.04286 -0.0897 0.7399 0.0111 -7.500 -0.3016 0.04228 0.03734 -0.0866 0.7386 0.0111 -7.250 -0.2979 0.03967 0.03447 -0.0844 0.7376 0.0116 -7.000 -0.2990 0.03544 0.02981 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-0.0036 0.0055 1.0000 14.750 1.1257 0.07581 0.06909 -0.0021 0.0055 1.0000 15.000 1.1223 0.07966 0.07325 -0.0013 0.0054 1.0000 15.250 1.1186 0.08326 0.07707 -0.0012 0.0054 1.0000 15.500 1.1096 0.08797 0.08206 -0.0010 0.0054 1.0000 15.750 1.1073 0.09147 0.08568 -0.0012 0.0055 1.0000 16.000 1.0921 0.09723 0.09173 -0.0018 0.0055 1.0000 16.250 1.0820 0.10214 0.09684 -0.0029 0.0055 1.0000 16.500 1.0712 0.10736 0.10225 -0.0042 0.0055 1.0000 16.750 1.0577 0.11331 0.10840 -0.0061 0.0055 1.0000 17.000 1.0426 0.11981 0.11510 -0.0086 0.0055 1.0000