GOE 441 AIRFOIL (goe441-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 441 AIRFOIL (goe441-il) Reynolds number: 500,000 Max Cl/Cd: 101.96 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe441-il-500000.txt Download as CSV file: xf-goe441-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 441 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
------ -------- --------- --------- -------- -------- --------
-10.250 0.0451 0.10288 0.09998 -0.0936 0.8529 0.0402
-10.000 0.0537 0.10033 0.09739 -0.0947 0.8423 0.0411
-9.750 0.0379 0.09439 0.09138 -0.1013 0.8326 0.0431
-9.500 0.0520 0.09225 0.08921 -0.1009 0.8231 0.0433
-9.250 0.0667 0.09035 0.08725 -0.1007 0.8140 0.0436
-9.000 0.0800 0.08842 0.08529 -0.1011 0.8048 0.0439
-8.750 -0.0653 0.02875 0.02477 -0.1756 0.8000 0.0385
-8.500 -0.0372 0.02570 0.02144 -0.1810 0.7927 0.0389
-8.250 -0.0089 0.02410 0.01969 -0.1836 0.7846 0.0394
-8.000 0.0200 0.02256 0.01793 -0.1860 0.7773 0.0398
-7.750 0.0499 0.02078 0.01589 -0.1885 0.7699 0.0402
-7.500 0.0796 0.01939 0.01424 -0.1903 0.7616 0.0406
-7.250 0.1094 0.01824 0.01287 -0.1917 0.7534 0.0410
-7.000 0.1391 0.01727 0.01168 -0.1927 0.7443 0.0415
-6.750 0.1689 0.01646 0.01066 -0.1936 0.7355 0.0421
-6.500 0.1986 0.01580 0.00981 -0.1943 0.7252 0.0426
-6.250 0.2281 0.01531 0.00913 -0.1948 0.7144 0.0430
-6.000 0.2569 0.01442 0.00812 -0.1954 0.7012 0.0439
-5.750 0.2855 0.01402 0.00767 -0.1956 0.6844 0.0447
-5.500 0.3137 0.01374 0.00727 -0.1958 0.6622 0.0458
-5.250 0.3408 0.01353 0.00685 -0.1956 0.6270 0.0468
-5.000 0.3664 0.01346 0.00648 -0.1952 0.5830 0.0478
-4.750 0.3929 0.01331 0.00610 -0.1951 0.5589 0.0487
-4.500 0.4210 0.01309 0.00579 -0.1953 0.5454 0.0501
-4.250 0.4493 0.01300 0.00560 -0.1954 0.5357 0.0517
-4.000 0.4781 0.01290 0.00540 -0.1956 0.5278 0.0536
-3.750 0.5067 0.01276 0.00517 -0.1959 0.5206 0.0559
-3.500 0.5362 0.01264 0.00504 -0.1962 0.5155 0.0590
-3.250 0.5657 0.01252 0.00490 -0.1965 0.5105 0.0631
-3.000 0.5945 0.01250 0.00482 -0.1966 0.5057 0.0684
-2.750 0.6228 0.01258 0.00485 -0.1967 0.5007 0.0753
-2.500 0.6520 0.01257 0.00487 -0.1969 0.4974 0.0836
-2.250 0.6809 0.01259 0.00490 -0.1970 0.4935 0.0915
-2.000 0.7096 0.01261 0.00491 -0.1971 0.4895 0.0990
-1.750 0.7376 0.01274 0.00496 -0.1971 0.4856 0.1055
-1.500 0.7663 0.01279 0.00498 -0.1974 0.4814 0.1123
-1.250 0.7952 0.01278 0.00497 -0.1975 0.4790 0.1181
-1.000 0.8245 0.01271 0.00492 -0.1978 0.4759 0.1248
-0.750 0.8532 0.01272 0.00493 -0.1980 0.4726 0.1312
-0.500 0.8818 0.01273 0.00493 -0.1981 0.4692 0.1387
-0.250 0.9100 0.01281 0.00499 -0.1982 0.4659 0.1468
0.000 0.9384 0.01297 0.00513 -0.1983 0.4622 0.1575
0.250 0.9671 0.01295 0.00520 -0.1985 0.4601 0.1743
0.500 0.9957 0.01295 0.00527 -0.1986 0.4573 0.2026
0.750 1.0242 0.01293 0.00533 -0.1988 0.4543 0.2351
1.000 1.0527 0.01292 0.00542 -0.1991 0.4513 0.2728
1.250 1.0811 0.01293 0.00558 -0.1993 0.4485 0.3457
1.500 1.1089 0.01307 0.00580 -0.1994 0.4453 0.4108
1.750 1.1366 0.01321 0.00600 -0.1994 0.4425 0.4502
2.000 1.1640 0.01328 0.00613 -0.1993 0.4400 0.4787
2.250 1.1912 0.01336 0.00626 -0.1992 0.4373 0.5011
2.500 1.2183 0.01346 0.00639 -0.1990 0.4344 0.5236
2.750 1.2450 0.01357 0.00653 -0.1989 0.4316 0.5439
3.000 1.2715 0.01372 0.00669 -0.1987 0.4287 0.5665
3.250 1.2985 0.01397 0.00695 -0.1986 0.4252 0.5934
3.500 1.3248 0.01399 0.00711 -0.1984 0.4229 0.6317
3.750 1.3508 0.01399 0.00733 -0.1981 0.4202 0.7071
4.000 1.3722 0.01379 0.00748 -0.1967 0.4175 0.8502
4.250 1.3949 0.01384 0.00756 -0.1957 0.4148 1.0000
4.500 1.4204 0.01405 0.00772 -0.1953 0.4120 1.0000
4.750 1.4459 0.01435 0.00794 -0.1950 0.4089 1.0000
5.000 1.4713 0.01458 0.00816 -0.1947 0.4062 1.0000
5.250 1.4960 0.01475 0.00836 -0.1942 0.4038 1.0000
5.500 1.5206 0.01494 0.00856 -0.1937 0.4011 1.0000
5.750 1.5447 0.01515 0.00876 -0.1931 0.3984 1.0000
6.000 1.5682 0.01538 0.00898 -0.1925 0.3957 1.0000
6.250 1.5913 0.01566 0.00923 -0.1918 0.3928 1.0000
6.500 1.6151 0.01600 0.00953 -0.1912 0.3897 1.0000
6.750 1.6354 0.01619 0.00978 -0.1899 0.3873 1.0000
7.000 1.6562 0.01642 0.01005 -0.1888 0.3845 1.0000
7.250 1.6771 0.01668 0.01033 -0.1877 0.3816 1.0000
7.500 1.6976 0.01698 0.01063 -0.1866 0.3788 1.0000
7.750 1.7179 0.01733 0.01096 -0.1855 0.3759 1.0000
8.000 1.7395 0.01774 0.01134 -0.1846 0.3729 1.0000
8.250 1.7584 0.01803 0.01172 -0.1833 0.3702 1.0000
8.500 1.7768 0.01836 0.01210 -0.1819 0.3666 1.0000
8.750 1.7942 0.01873 0.01249 -0.1804 0.3627 1.0000
9.000 1.8106 0.01923 0.01294 -0.1789 0.3583 1.0000
9.250 1.8279 0.01968 0.01345 -0.1775 0.3544 1.0000
9.500 1.8453 0.02011 0.01395 -0.1761 0.3503 1.0000
9.750 1.8612 0.02063 0.01449 -0.1746 0.3460 1.0000
10.000 1.8754 0.02130 0.01513 -0.1729 0.3414 1.0000
10.250 1.8919 0.02185 0.01576 -0.1716 0.3374 1.0000
10.500 1.9079 0.02244 0.01641 -0.1703 0.3327 1.0000
10.750 1.9210 0.02321 0.01718 -0.1686 0.3278 1.0000
11.000 1.9339 0.02403 0.01802 -0.1670 0.3226 1.0000
11.250 1.9483 0.02479 0.01884 -0.1656 0.3169 1.0000
11.500 1.9590 0.02578 0.01984 -0.1639 0.3114 1.0000
11.750 1.9708 0.02676 0.02086 -0.1624 0.3061 1.0000
12.000 1.9829 0.02775 0.02190 -0.1609 0.3001 1.0000
12.250 1.9897 0.02911 0.02325 -0.1590 0.2942 1.0000
12.500 2.0008 0.03023 0.02444 -0.1576 0.2879 1.0000
12.750 2.0059 0.03182 0.02603 -0.1557 0.2805 1.0000
13.000 2.0133 0.03329 0.02754 -0.1541 0.2737 1.0000
13.250 2.0168 0.03511 0.02939 -0.1523 0.2662 1.0000
13.500 2.0201 0.03703 0.03133 -0.1506 0.2585 1.0000
13.750 2.0186 0.03944 0.03375 -0.1488 0.2499 1.0000
14.000 2.0191 0.04175 0.03609 -0.1471 0.2410 1.0000
14.250 2.0127 0.04477 0.03912 -0.1452 0.2324 1.0000
14.500 2.0064 0.04791 0.04228 -0.1435 0.2222 1.0000
14.750 1.9950 0.05168 0.04607 -0.1418 0.2109 1.0000
15.000 1.9784 0.05616 0.05055 -0.1401 0.1992 1.0000
15.250 1.9576 0.06128 0.05570 -0.1386 0.1870 1.0000
15.500 1.9318 0.06730 0.06172 -0.1375 0.1738 1.0000
15.750 1.9020 0.07405 0.06850 -0.1367 0.1600 1.0000
16.000 1.8690 0.08144 0.07591 -0.1362 0.1464 1.0000
16.250 1.8350 0.08909 0.08358 -0.1361 0.1341 1.0000
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