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 = 0.030 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -2.500 -0.1223 0.05425 0.04684 -0.0316 1.0002 0.3602 -2.250 -0.0797 0.05127 0.04346 -0.0382 1.0002 0.3159 -2.000 -0.0469 0.04912 0.04101 -0.0415 1.0002 0.2923 -1.750 -0.0154 0.04758 0.03910 -0.0442 1.0002 0.2738 -1.500 0.0123 0.04635 0.03753 -0.0458 1.0002 0.2588 -1.250 0.0347 0.04551 0.03653 -0.0462 1.0002 0.2499 -1.000 0.0580 0.04502 0.03577 -0.0469 1.0002 0.2410 -0.750 0.0800 0.04528 0.03566 -0.0474 1.0002 0.2344 -0.500 0.0987 0.04552 0.03578 -0.0478 1.0002 0.2328 -0.250 0.1161 0.04629 0.03639 -0.0485 1.0002 0.2326 0.000 0.1307 0.04750 0.03748 -0.0493 1.0002 0.2328 0.250 0.1455 0.04900 0.03887 -0.0507 0.9990 0.2331 0.500 0.2733 0.04698 0.03640 -0.0683 0.9509 0.2370 0.750 0.4175 0.04221 0.03185 -0.0856 0.8895 0.2732 1.000 0.5110 0.03465 0.02663 -0.0888 0.8170 0.9998 1.250 0.5580 0.03328 0.02417 -0.0845 0.7496 0.9998 1.500 0.5847 0.03328 0.02334 -0.0792 0.6869 0.9998 1.750 0.6068 0.03384 0.02313 -0.0743 0.6223 0.9998 2.000 0.6281 0.03486 0.02342 -0.0702 0.5560 0.9998 2.250 0.6511 0.03611 0.02390 -0.0672 0.5007 0.9998 2.500 0.6766 0.03772 0.02501 -0.0657 0.4593 0.9998 2.750 0.7041 0.03958 0.02660 -0.0653 0.4309 0.9998 3.000 0.7322 0.04151 0.02832 -0.0653 0.4107 0.9998 3.250 0.7593 0.04350 0.03018 -0.0654 0.3942 0.9998 3.500 0.7859 0.04533 0.03177 -0.0652 0.3803 0.9998 3.750 0.8116 0.04732 0.03370 -0.0653 0.3676 0.9998 4.000 0.8359 0.04996 0.03640 -0.0657 0.3589 0.9998 4.250 0.8582 0.05306 0.03970 -0.0665 0.3526 0.9998 4.500 0.8813 0.05586 0.04252 -0.0668 0.3477 0.9998 4.750 0.9054 0.05860 0.04512 -0.0669 0.3439 0.9998 5.000 0.9171 0.06337 0.05028 -0.0680 0.3423 0.9998