XFOIL Version 6.96 Calculated polar for: GOE 798 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.750 -0.6851 0.05254 0.04857 -0.1457 0.9813 0.0493 -15.500 -0.7056 0.04442 0.04015 -0.1552 0.9759 0.0495 -15.250 -0.7146 0.03940 0.03489 -0.1607 0.9683 0.0497 -15.000 -0.7200 0.03589 0.03124 -0.1626 0.9608 0.0501 -14.750 -0.7191 0.03368 0.02895 -0.1627 0.9524 0.0505 -14.500 -0.7161 0.03196 0.02716 -0.1622 0.9444 0.0508 -14.250 -0.7128 0.03050 0.02563 -0.1610 0.9358 0.0511 -14.000 -0.7079 0.02924 0.02428 -0.1596 0.9276 0.0515 -13.750 -0.7026 0.02810 0.02305 -0.1577 0.9187 0.0519 -13.500 -0.6965 0.02708 0.02192 -0.1555 0.9101 0.0524 -13.250 -0.6914 0.02622 0.02094 -0.1528 0.9006 0.0528 -13.000 -0.6804 0.02533 0.01992 -0.1510 0.8920 0.0533 -12.750 -0.6673 0.02448 0.01893 -0.1494 0.8826 0.0539 -12.500 -0.6519 0.02371 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0.00473 -0.1358 0.6057 0.4211 2.000 0.8484 0.01085 0.00485 -0.1344 0.6020 0.6077 2.250 0.8655 0.01036 0.00500 -0.1321 0.5977 0.8001 2.500 0.9020 0.01034 0.00527 -0.1333 0.5929 0.9498 2.750 0.9448 0.01053 0.00537 -0.1365 0.5877 0.9795 3.000 0.9968 0.01071 0.00555 -0.1418 0.5821 0.9930 3.250 1.0489 0.01086 0.00567 -0.1473 0.5757 1.0000 3.500 1.0662 0.01095 0.00569 -0.1452 0.5702 1.0000 3.750 1.0824 0.01104 0.00576 -0.1429 0.5646 1.0000 4.000 1.0971 0.01112 0.00584 -0.1404 0.5580 1.0000 4.250 1.1106 0.01124 0.00589 -0.1375 0.5515 1.0000 4.500 1.1228 0.01135 0.00600 -0.1344 0.5445 1.0000 4.750 1.1289 0.01147 0.00609 -0.1300 0.5366 1.0000 5.000 1.1384 0.01165 0.00623 -0.1265 0.5286 1.0000 5.250 1.1496 0.01186 0.00642 -0.1233 0.5185 1.0000 5.500 1.1617 0.01215 0.00666 -0.1204 0.5074 1.0000 5.750 1.1721 0.01254 0.00697 -0.1174 0.4944 1.0000 6.000 1.1828 0.01300 0.00736 -0.1145 0.4794 1.0000 6.250 1.1930 0.01355 0.00783 -0.1116 0.4634 1.0000 6.500 1.2026 0.01419 0.00839 -0.1088 0.4471 1.0000 6.750 1.2116 0.01492 0.00903 -0.1059 0.4315 1.0000 7.000 1.2210 0.01570 0.00972 -0.1033 0.4177 1.0000 7.500 1.2444 0.01721 0.01113 -0.0991 0.3967 1.0000 7.750 1.2550 0.01807 0.01191 -0.0969 0.3884 1.0000 8.000 1.2709 0.01872 0.01256 -0.0955 0.3819 1.0000 8.250 1.2849 0.01947 0.01328 -0.0940 0.3757 1.0000 8.500 1.2963 0.02038 0.01413 -0.0921 0.3699 1.0000 8.750 1.3139 0.02099 0.01476 -0.0911 0.3656 1.0000 9.000 1.3301 0.02168 0.01546 -0.0900 0.3612 1.0000 9.250 1.3443 0.02250 0.01626 -0.0887 0.3572 1.0000 9.500 1.3575 0.02338 0.01710 -0.0872 0.3530 1.0000 9.750 1.3745 0.02408 0.01782 -0.0863 0.3497 1.0000 10.000 1.3912 0.02481 0.01859 -0.0854 0.3464 1.0000 10.250 1.4069 0.02560 0.01940 -0.0844 0.3428 1.0000 10.500 1.4212 0.02649 0.02027 -0.0833 0.3392 1.0000 10.750 1.4351 0.02740 0.02116 -0.0822 0.3357 1.0000 11.000 1.4518 0.02815 0.02191 -0.0813 0.3329 1.0000 11.250 1.4680 0.02898 0.02280 -0.0806 0.3303 1.0000 11.500 1.4834 0.02987 0.02374 -0.0798 0.3273 1.0000 11.750 1.4984 0.03077 0.02466 -0.0789 0.3243 1.0000 12.000 1.5123 0.03175 0.02564 -0.0780 0.3212 1.0000 12.250 1.5266 0.03267 0.02654 -0.0770 0.3179 1.0000 12.500 1.5426 0.03350 0.02740 -0.0763 0.3152 1.0000 12.750 1.5570 0.03452 0.02850 -0.0756 0.3128 1.0000 13.000 1.5705 0.03563 0.02966 -0.0749 0.3098 1.0000 13.250 1.5836 0.03674 0.03081 -0.0741 0.3066 1.0000 13.500 1.5956 0.03792 0.03200 -0.0732 0.3032 1.0000 13.750 1.6087 0.03893 0.03298 -0.0723 0.2994 1.0000 14.000 1.6209 0.04018 0.03431 -0.0716 0.2967 1.0000 14.250 1.6324 0.04153 0.03574 -0.0709 0.2935 1.0000 14.500 1.6426 0.04297 0.03724 -0.0702 0.2897 1.0000 14.750 1.6520 0.04444 0.03871 -0.0693 0.2856 1.0000 15.000 1.6608 0.04593 0.04020 -0.0684 0.2813 1.0000 15.250 1.6702 0.04754 0.04193 -0.0678 0.2774 1.0000 15.500 1.6781 0.04926 0.04370 -0.0671 0.2724 1.0000 15.750 1.6822 0.05128 0.04571 -0.0661 0.2671 1.0000 16.000 1.6898 0.05308 0.04759 -0.0654 0.2615 1.0000 16.250 1.6933 0.05530 0.04985 -0.0647 0.2546 1.0000 16.500 1.6948 0.05770 0.05226 -0.0638 0.2470 1.0000 16.750 1.6935 0.06042 0.05500 -0.0629 0.2371 1.0000 17.000 1.6912 0.06327 0.05786 -0.0620 0.2263 1.0000 17.250 1.6854 0.06648 0.06104 -0.0610 0.2151 1.0000 17.500 1.6753 0.07019 0.06471 -0.0599 0.2047 1.0000 17.750 1.6700 0.07342 0.06793 -0.0591 0.1960 1.0000 18.000 1.6633 0.07678 0.07128 -0.0583 0.1892 1.0000 18.250 1.6589 0.07995 0.07447 -0.0577 0.1836 1.0000 18.500 1.6522 0.08338 0.07788 -0.0571 0.1785 1.0000 18.750 1.6529 0.08606 0.08062 -0.0568 0.1750 1.0000 19.000 1.6521 0.08891 0.08350 -0.0565 0.1713 1.0000 19.250 1.6475 0.09216 0.08676 -0.0562 0.1676 1.0000