XFOIL Version 6.96 Calculated polar for: GOE 449 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.750 -0.6807 0.07340 0.07085 -0.1092 0.9942 0.0264 -16.500 -0.7311 0.06027 0.05748 -0.1202 0.9914 0.0263 -16.250 -0.7502 0.05173 0.04875 -0.1288 0.9882 0.0264 -16.000 -0.7600 0.04448 0.04131 -0.1372 0.9850 0.0265 -15.750 -0.7573 0.03912 0.03577 -0.1445 0.9824 0.0267 -15.500 -0.7551 0.03533 0.03184 -0.1486 0.9762 0.0268 -15.250 -0.7456 0.03232 0.02869 -0.1524 0.9713 0.0270 -15.000 -0.7303 0.03006 0.02629 -0.1557 0.9664 0.0271 -14.750 -0.7212 0.02718 0.02323 -0.1589 0.9586 0.0274 -14.500 -0.6979 0.02479 0.02071 -0.1632 0.9545 0.0277 -14.250 -0.6732 0.02328 0.01910 -0.1660 0.9466 0.0280 -14.000 -0.6409 0.02218 0.01794 -0.1693 0.9403 0.0284 -13.750 -0.6168 0.02127 0.01693 -0.1706 0.9297 0.0287 -13.500 -0.5939 0.02053 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0.00691 0.00221 -0.0970 0.5742 0.7102 1.000 0.5892 0.00685 0.00231 -0.0942 0.5663 0.7691 1.250 0.6010 0.00684 0.00246 -0.0907 0.5584 0.8344 1.500 0.6207 0.00686 0.00261 -0.0888 0.5523 0.8892 1.750 0.6407 0.00698 0.00274 -0.0871 0.5454 0.9203 2.000 0.6677 0.00711 0.00287 -0.0869 0.5392 0.9412 2.250 0.7053 0.00727 0.00301 -0.0891 0.5314 0.9578 2.500 0.7540 0.00755 0.00322 -0.0938 0.5233 0.9713 2.750 0.7991 0.00772 0.00337 -0.0976 0.5183 0.9783 3.000 0.8400 0.00792 0.00354 -0.1006 0.5133 0.9831 3.250 0.8789 0.00815 0.00371 -0.1032 0.5081 0.9870 3.500 0.9153 0.00830 0.00384 -0.1052 0.5037 0.9908 3.750 0.9523 0.00844 0.00397 -0.1074 0.4990 0.9943 4.000 0.9908 0.00862 0.00411 -0.1099 0.4937 0.9974 4.250 1.0296 0.00882 0.00427 -0.1126 0.4881 0.9996 4.500 1.0454 0.00887 0.00433 -0.1104 0.4843 1.0000 4.750 1.0516 0.00893 0.00439 -0.1062 0.4801 1.0000 5.000 1.0584 0.00905 0.00449 -0.1021 0.4755 1.0000 5.250 1.0693 0.00920 0.00461 -0.0989 0.4702 1.0000 5.500 1.0870 0.00930 0.00473 -0.0970 0.4652 1.0000 5.750 1.1033 0.00947 0.00488 -0.0950 0.4602 1.0000 6.000 1.1183 0.00971 0.00509 -0.0927 0.4550 1.0000 6.250 1.1388 0.00985 0.00524 -0.0915 0.4505 1.0000 6.500 1.1575 0.01003 0.00543 -0.0900 0.4450 1.0000 6.750 1.1725 0.01034 0.00569 -0.0878 0.4379 1.0000 7.000 1.1929 0.01052 0.00589 -0.0867 0.4314 1.0000 7.250 1.2099 0.01082 0.00616 -0.0850 0.4241 1.0000 7.500 1.2276 0.01111 0.00644 -0.0834 0.4170 1.0000 7.750 1.2452 0.01142 0.00674 -0.0819 0.4085 1.0000 8.000 1.2616 0.01179 0.00709 -0.0803 0.4002 1.0000 8.250 1.2775 0.01221 0.00747 -0.0786 0.3899 1.0000 8.500 1.2938 0.01263 0.00787 -0.0770 0.3800 1.0000 8.750 1.3076 0.01316 0.00837 -0.0751 0.3692 1.0000 9.000 1.3224 0.01369 0.00886 -0.0734 0.3576 1.0000 9.250 1.3370 0.01425 0.00940 -0.0718 0.3466 1.0000 9.500 1.3498 0.01491 0.01001 -0.0699 0.3349 1.0000 9.750 1.3620 0.01562 0.01067 -0.0681 0.3232 1.0000 10.000 1.3760 0.01627 0.01130 -0.0665 0.3122 1.0000 10.250 1.3875 0.01708 0.01207 -0.0647 0.3003 1.0000 10.500 1.3979 0.01796 0.01290 -0.0628 0.2884 1.0000 10.750 1.4083 0.01887 0.01376 -0.0610 0.2757 1.0000 11.000 1.4208 0.01969 0.01456 -0.0595 0.2660 1.0000 11.250 1.4304 0.02070 0.01554 -0.0577 0.2556 1.0000 11.500 1.4387 0.02182 0.01661 -0.0559 0.2435 1.0000 11.750 1.4504 0.02276 0.01753 -0.0545 0.2344 1.0000 12.000 1.4586 0.02394 0.01868 -0.0528 0.2252 1.0000 12.250 1.4692 0.02499 0.01972 -0.0515 0.2161 1.0000 12.500 1.4782 0.02620 0.02091 -0.0500 0.2079 1.0000 12.750 1.4871 0.02740 0.02210 -0.0486 0.1992 1.0000 13.000 1.4954 0.02870 0.02338 -0.0472 0.1904 1.0000 13.250 1.5022 0.03012 0.02477 -0.0457 0.1820 1.0000 13.500 1.5091 0.03159 0.02623 -0.0444 0.1720 1.0000 13.750 1.5148 0.03315 0.02777 -0.0430 0.1633 1.0000 14.000 1.5170 0.03501 0.02959 -0.0414 0.1528 1.0000 14.250 1.5230 0.03665 0.03123 -0.0402 0.1457 1.0000 14.500 1.5264 0.03850 0.03306 -0.0389 0.1387 1.0000 14.750 1.5324 0.04021 0.03479 -0.0379 0.1341 1.0000 15.000 1.5352 0.04218 0.03677 -0.0367 0.1286 1.0000 15.250 1.5408 0.04398 0.03859 -0.0358 0.1247 1.0000 15.500 1.5462 0.04581 0.04045 -0.0350 0.1212 1.0000 15.750 1.5494 0.04788 0.04253 -0.0341 0.1176 1.0000 16.000 1.5520 0.05004 0.04474 -0.0332 0.1141 1.0000 16.250 1.5593 0.05178 0.04652 -0.0327 0.1113 1.0000 16.500 1.5622 0.05396 0.04874 -0.0320 0.1080 1.0000 16.750 1.5629 0.05639 0.05118 -0.0313 0.1046 1.0000 17.000 1.5668 0.05855 0.05339 -0.0308 0.1018 1.0000 17.250 1.5715 0.06064 0.05553 -0.0304 0.0986 1.0000 17.500 1.5723 0.06313 0.05804 -0.0300 0.0947 1.0000 17.750 1.5721 0.06578 0.06072 -0.0296 0.0913 1.0000 18.000 1.5756 0.06805 0.06303 -0.0293 0.0876 1.0000 18.250 1.5723 0.07108 0.06606 -0.0290 0.0823 1.0000 18.500 1.5716 0.07387 0.06888 -0.0288 0.0774 1.0000 18.750 1.5660 0.07718 0.07219 -0.0286 0.0713 1.0000 19.000 1.5589 0.08072 0.07573 -0.0284 0.0654 1.0000 19.250 1.5526 0.08424 0.07927 -0.0284 0.0607 1.0000