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 = 0.045 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 0.0647 0.05203 0.04663 -0.0024 1.0002 0.9770 -2.750 -0.0001 0.05256 0.04739 0.0120 1.0002 0.9313 -2.500 -0.0594 0.05245 0.04752 0.0237 1.0002 0.8890 -2.250 -0.1195 0.05222 0.04757 0.0353 1.0002 0.8631 -2.000 -0.1753 0.05155 0.04716 0.0460 1.0002 0.8433 -1.750 -0.2275 0.05072 0.04657 0.0552 1.0002 0.8252 -1.250 0.0328 0.04432 0.03643 -0.0459 1.0002 0.2144 -1.000 0.0513 0.04334 0.03552 -0.0463 1.0002 0.2064 -0.750 0.0732 0.04390 0.03566 -0.0472 1.0002 0.1951 -0.500 0.1512 0.04143 0.03291 -0.0569 0.9823 0.1852 -0.250 0.2462 0.03891 0.02971 -0.0678 0.9544 0.1735 0.000 0.3446 0.03489 0.02548 -0.0780 0.9191 0.1771 0.250 0.4277 0.03123 0.02167 -0.0832 0.8731 0.1821 0.500 0.4714 0.02954 0.01978 -0.0819 0.8168 0.1884 0.750 0.4999 0.02879 0.01883 -0.0788 0.7599 0.1996 1.000 0.5240 0.02842 0.01824 -0.0754 0.7012 0.2178 1.250 0.5477 0.02805 0.01782 -0.0725 0.6400 0.2590 1.500 0.5634 0.02589 0.01698 -0.0674 0.5832 0.9998 1.750 0.5873 0.02676 0.01694 -0.0646 0.5135 0.9998 2.000 0.6116 0.02802 0.01721 -0.0625 0.4445 0.9998 2.250 0.6387 0.02950 0.01797 -0.0615 0.3898 0.9998 2.500 0.6669 0.03087 0.01879 -0.0611 0.3573 0.9998 2.750 0.6953 0.03213 0.01968 -0.0610 0.3345 0.9998 3.000 0.7239 0.03342 0.02066 -0.0609 0.3186 0.9998 3.250 0.7528 0.03475 0.02172 -0.0610 0.3070 0.9998 3.500 0.7816 0.03632 0.02327 -0.0613 0.2979 0.9998 3.750 0.8101 0.03781 0.02469 -0.0614 0.2902 0.9998 4.000 0.8383 0.03948 0.02609 -0.0616 0.2844 0.9998 4.250 0.8651 0.04135 0.02827 -0.0619 0.2783 0.9998 4.500 0.8916 0.04302 0.02998 -0.0620 0.2721 0.9998 4.750 0.9184 0.04456 0.03132 -0.0621 0.2667 0.9998 5.000 0.9425 0.04684 0.03378 -0.0623 0.2625 0.9998