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 = 0.026 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -2.750 -0.1856 0.05889 0.05154 -0.0161 1.0002 0.4150 -2.500 -0.1260 0.05507 0.04716 -0.0304 1.0002 0.3551 -2.250 -0.0839 0.05225 0.04394 -0.0373 1.0002 0.3238 -1.750 -0.0198 0.04851 0.03959 -0.0432 1.0002 0.2872 -1.500 0.0101 0.04742 0.03808 -0.0453 1.0002 0.2739 -1.250 0.0336 0.04644 0.03692 -0.0459 1.0002 0.2664 -1.000 0.0577 0.04600 0.03616 -0.0467 1.0002 0.2615 -0.750 0.0799 0.04596 0.03584 -0.0472 1.0002 0.2595 -0.500 0.1006 0.04627 0.03590 -0.0478 1.0002 0.2585 -0.250 0.1199 0.04695 0.03638 -0.0484 1.0002 0.2577 0.000 0.1363 0.04803 0.03730 -0.0491 1.0002 0.2570 0.250 0.1499 0.04943 0.03863 -0.0499 1.0002 0.2570 0.500 0.1614 0.05114 0.04032 -0.0509 1.0002 0.2578 0.750 0.2469 0.05122 0.04034 -0.0637 0.9699 0.2711 1.000 0.3823 0.04827 0.03774 -0.0817 0.8995 0.3150 1.250 0.5374 0.03932 0.02996 -0.0912 0.8046 0.9998 1.500 0.5863 0.03772 0.02743 -0.0867 0.7292 0.9998 1.750 0.6139 0.03768 0.02665 -0.0811 0.6637 0.9998 2.000 0.6362 0.03858 0.02690 -0.0764 0.6008 0.9998 2.250 0.6590 0.03981 0.02750 -0.0726 0.5465 0.9998 2.500 0.6830 0.04124 0.02834 -0.0701 0.5041 0.9998 2.750 0.7073 0.04326 0.03013 -0.0692 0.4710 0.9998 3.000 0.7341 0.04543 0.03209 -0.0690 0.4492 0.9998 3.250 0.7601 0.04800 0.03460 -0.0695 0.4328 0.9998 3.500 0.7858 0.05036 0.03680 -0.0695 0.4195 0.9998 3.750 0.8096 0.05281 0.03918 -0.0696 0.4066 0.9998 4.000 0.8293 0.05606 0.04253 -0.0702 0.3959 0.9998 4.250 0.8513 0.05865 0.04506 -0.0702 0.3867 0.9998 4.500 0.8698 0.06230 0.04874 -0.0708 0.3818 0.9998 4.750 0.8764 0.06769 0.05443 -0.0723 0.3800 0.9998 5.000 0.8781 0.07352 0.06048 -0.0737 0.3800 0.9998