XFOIL Version 6.94 Calculated polar for: Eif385mod 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.030 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.0928 0.04031 0.02678 -0.0266 0.9993 0.3952 -2.750 -0.0659 0.04004 0.02635 -0.0269 0.9993 0.3969 -2.500 -0.0393 0.03988 0.02607 -0.0272 0.9993 0.4004 -2.250 -0.0133 0.03982 0.02594 -0.0274 0.9993 0.4081 -2.000 0.0123 0.03984 0.02593 -0.0275 0.9993 0.4170 -1.750 0.0371 0.03985 0.02604 -0.0276 0.9993 0.4265 -1.500 0.0615 0.04008 0.02629 -0.0277 0.9993 0.4353 -1.250 0.0849 0.04025 0.02668 -0.0276 0.9993 0.4488 -1.000 0.1078 0.04049 0.02721 -0.0276 0.9993 0.4697 -0.750 0.1302 0.04074 0.02792 -0.0277 0.9993 0.4995 -0.500 0.1504 0.04053 0.02881 -0.0269 0.9993 0.6030 -0.250 0.1557 0.04063 0.02945 -0.0247 0.9993 1.0007 0.000 0.1734 0.04208 0.03075 -0.0248 0.9993 1.0007 0.250 0.1880 0.04384 0.03241 -0.0249 0.9993 1.0007 0.500 0.2507 0.04559 0.03399 -0.0345 0.9776 1.0007 0.750 0.3790 0.04519 0.03339 -0.0539 0.9087 1.0007 1.000 0.5059 0.04244 0.03055 -0.0696 0.8329 1.0007 1.250 0.5930 0.03966 0.02764 -0.0763 0.7738 1.0007 1.500 0.6486 0.03827 0.02601 -0.0782 0.7309 1.0007 1.750 0.6835 0.03846 0.02600 -0.0782 0.6968 1.0007 2.000 0.7155 0.03906 0.02644 -0.0783 0.6715 1.0007 2.250 0.7472 0.03984 0.02706 -0.0786 0.6519 1.0007 2.500 0.7773 0.04089 0.02799 -0.0791 0.6359 1.0007 2.750 0.8037 0.04229 0.02936 -0.0794 0.6216 1.0007 3.000 0.8264 0.04407 0.03114 -0.0796 0.6084 1.0007 3.250 0.8458 0.04622 0.03333 -0.0797 0.5968 1.0007 3.500 0.8670 0.04828 0.03541 -0.0799 0.5875 1.0007 3.750 0.8831 0.05098 0.03822 -0.0801 0.5802 1.0007 4.000 0.9012 0.05362 0.04091 -0.0805 0.5749 1.0007 4.250 0.8884 0.05920 0.04666 -0.0793 0.5709 1.0007 4.500 0.8666 0.06557 0.05313 -0.0777 0.5691 1.0007 4.750 0.8287 0.07324 0.06085 -0.0754 0.5698 1.0007 5.000 0.7939 0.08054 0.06815 -0.0735 0.5721 1.0007