XFOIL Version 6.94 Calculated polar for: GOEN 611 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.040 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -2.750 -0.0918 0.05618 0.05082 0.0269 1.0002 0.8659 -2.500 -0.1460 0.05548 0.05040 0.0362 1.0002 0.8284 -2.250 -0.2016 0.05471 0.04991 0.0462 1.0002 0.8071 -2.000 -0.2530 0.05374 0.04918 0.0534 1.0002 0.7828 -1.500 0.0123 0.04513 0.03719 -0.0456 1.0002 0.2345 -1.250 0.0317 0.04397 0.03603 -0.0458 1.0002 0.2257 -1.000 0.0559 0.04415 0.03573 -0.0467 1.0002 0.2134 -0.750 0.0744 0.04390 0.03549 -0.0472 1.0002 0.2085 -0.500 0.0921 0.04434 0.03580 -0.0480 1.0002 0.2016 -0.250 0.1729 0.04289 0.03376 -0.0582 0.9795 0.1907 0.000 0.2704 0.04019 0.03064 -0.0698 0.9457 0.1908 0.250 0.3871 0.03581 0.02594 -0.0817 0.9039 0.1955 0.500 0.4662 0.03195 0.02205 -0.0853 0.8494 0.2091 0.750 0.5032 0.03044 0.02045 -0.0827 0.7892 0.2281 1.000 0.5296 0.02980 0.01976 -0.0793 0.7302 0.2565 1.250 0.5452 0.02712 0.01891 -0.0738 0.6746 0.9998 1.500 0.5688 0.02761 0.01845 -0.0697 0.6119 0.9998 1.750 0.5914 0.02837 0.01824 -0.0661 0.5453 0.9998 2.000 0.6147 0.02959 0.01859 -0.0636 0.4743 0.9998 2.250 0.6408 0.03108 0.01928 -0.0622 0.4206 0.9998 2.500 0.6691 0.03255 0.02021 -0.0617 0.3854 0.9998 2.750 0.6976 0.03398 0.02125 -0.0615 0.3612 0.9998 3.000 0.7259 0.03533 0.02225 -0.0614 0.3429 0.9998 3.250 0.7541 0.03673 0.02354 -0.0615 0.3279 0.9998 3.500 0.7826 0.03846 0.02521 -0.0617 0.3179 0.9998 3.750 0.8107 0.04011 0.02681 -0.0619 0.3096 0.9998 4.000 0.8387 0.04196 0.02847 -0.0621 0.3035 0.9998 4.250 0.8647 0.04424 0.03106 -0.0625 0.2979 0.9998 4.500 0.8902 0.04633 0.03325 -0.0628 0.2921 0.9998 4.750 0.9165 0.04806 0.03481 -0.0628 0.2867 0.9998 5.000 0.9389 0.05067 0.03760 -0.0629 0.2820 0.9998