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 = 0.045 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.0906 0.03853 0.02668 -0.0266 0.9993 0.3172 -2.750 -0.0662 0.03841 0.02640 -0.0265 0.9993 0.3191 -2.500 -0.0425 0.03798 0.02594 -0.0265 0.9993 0.3215 -2.250 -0.0191 0.03786 0.02576 -0.0263 0.9993 0.3230 -2.000 0.0046 0.03791 0.02574 -0.0261 0.9993 0.3244 -1.750 0.0288 0.03810 0.02587 -0.0261 0.9993 0.3268 -1.500 0.0524 0.03839 0.02614 -0.0261 0.9993 0.3304 -1.250 0.0752 0.03880 0.02654 -0.0261 0.9993 0.3372 -1.000 0.0974 0.03932 0.02709 -0.0261 0.9993 0.3443 -0.750 0.1195 0.03981 0.02774 -0.0262 0.9993 0.3518 -0.500 0.1682 0.04002 0.02806 -0.0312 0.9906 0.3636 -0.250 0.2425 0.03913 0.02749 -0.0407 0.9683 0.3895 0.250 0.3987 0.03432 0.02481 -0.0583 0.9101 1.0007 0.500 0.4854 0.03175 0.02215 -0.0669 0.8708 1.0007 0.750 0.5559 0.02883 0.01917 -0.0709 0.8154 1.0007 1.000 0.6084 0.02659 0.01659 -0.0709 0.7319 1.0007 1.250 0.6409 0.02636 0.01568 -0.0692 0.6523 1.0007 1.500 0.6692 0.02695 0.01571 -0.0682 0.6053 1.0007 1.750 0.6980 0.02774 0.01613 -0.0680 0.5748 1.0007 2.000 0.7271 0.02859 0.01675 -0.0683 0.5520 1.0007 2.250 0.7564 0.02944 0.01742 -0.0686 0.5348 1.0007 2.500 0.7855 0.03034 0.01820 -0.0691 0.5209 1.0007 2.750 0.8151 0.03126 0.01895 -0.0696 0.5103 1.0007 3.000 0.8432 0.03234 0.02009 -0.0702 0.5010 1.0007 3.250 0.8730 0.03338 0.02099 -0.0708 0.4941 1.0007 3.500 0.8997 0.03467 0.02247 -0.0715 0.4875 1.0007 3.750 0.9271 0.03595 0.02381 -0.0721 0.4819 1.0007 4.000 0.9553 0.03723 0.02508 -0.0728 0.4773 1.0007 4.250 0.9807 0.03879 0.02679 -0.0734 0.4727 1.0007 4.500 1.0041 0.04048 0.02872 -0.0738 0.4676 1.0007 4.750 1.0285 0.04209 0.03044 -0.0741 0.4628 1.0007 5.000 1.0537 0.04375 0.03219 -0.0746 0.4592 1.0007