GOE 549 AIRFOIL (goe549-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 549 AIRFOIL (goe549-il) Reynolds number: 50,000 Max Cl/Cd: 26.37 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe549-il-50000-n5.txt Download as CSV file: xf-goe549-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 549 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2991 0.10532 0.09895 -0.0480 1.0000 0.0762
-9.000 -0.2957 0.10329 0.09700 -0.0451 1.0000 0.0752
-8.750 -0.3042 0.10170 0.09553 -0.0425 1.0000 0.0744
-8.500 -0.3012 0.09833 0.09221 -0.0446 0.9937 0.0738
-8.250 -0.2860 0.09352 0.08740 -0.0501 0.9820 0.0726
-8.000 -0.2747 0.08858 0.08247 -0.0559 0.9683 0.0718
-7.750 -0.2658 0.08338 0.07727 -0.0622 0.9538 0.0701
-7.250 -0.2677 0.06536 0.05880 -0.0850 0.9204 0.0641
-7.000 -0.2529 0.06056 0.05377 -0.0892 0.9088 0.0637
-6.750 -0.2374 0.05550 0.04833 -0.0935 0.8983 0.0636
-6.500 -0.2260 0.05103 0.04329 -0.0959 0.8854 0.0644
-6.250 -0.2063 0.04867 0.04089 -0.0966 0.8739 0.0660
-6.000 -0.1851 0.04585 0.03776 -0.0978 0.8641 0.0672
-5.750 -0.1639 0.04284 0.03428 -0.0986 0.8543 0.0676
-5.500 -0.1450 0.04050 0.03153 -0.0984 0.8431 0.0681
-5.250 -0.1176 0.03821 0.02881 -0.0992 0.8357 0.0696
-5.000 -0.0975 0.03670 0.02695 -0.0984 0.8249 0.0723
-4.750 -0.0725 0.03508 0.02487 -0.0982 0.8163 0.0746
-4.500 -0.0462 0.03358 0.02294 -0.0979 0.8079 0.0760
-4.250 -0.0214 0.03235 0.02154 -0.0975 0.7995 0.0775
-4.000 0.0056 0.03129 0.02036 -0.0973 0.7920 0.0796
-3.750 0.0304 0.03051 0.01943 -0.0967 0.7839 0.0829
-3.500 0.0571 0.02980 0.01850 -0.0963 0.7764 0.0880
-3.250 0.0822 0.02912 0.01775 -0.0957 0.7691 0.0927
-3.000 0.1072 0.02853 0.01705 -0.0951 0.7614 0.0980
-2.750 0.1357 0.02792 0.01625 -0.0950 0.7551 0.1054
-2.500 0.1575 0.02747 0.01578 -0.0942 0.7469 0.1167
-2.250 0.1874 0.02653 0.01494 -0.0945 0.7418 0.1506
-2.000 0.2045 0.02579 0.01490 -0.0935 0.7329 0.2679
-1.750 0.2280 0.02499 0.01483 -0.0924 0.7275 0.4562
-1.500 0.2416 0.02487 0.01518 -0.0895 0.7195 0.5965
-1.250 0.2613 0.02437 0.01517 -0.0863 0.7137 0.7401
-1.000 0.3623 0.02365 0.01450 -0.0980 0.7092 0.9977
-0.750 0.3781 0.02400 0.01456 -0.0967 0.7008 1.0000
-0.500 0.4060 0.02400 0.01421 -0.0967 0.6956 1.0000
-0.250 0.4203 0.02453 0.01454 -0.0950 0.6866 1.0000
0.000 0.4489 0.02458 0.01430 -0.0950 0.6811 1.0000
0.250 0.4658 0.02510 0.01464 -0.0935 0.6726 1.0000
0.500 0.4936 0.02522 0.01453 -0.0934 0.6667 1.0000
0.750 0.5131 0.02569 0.01484 -0.0922 0.6589 1.0000
1.000 0.5387 0.02593 0.01490 -0.0918 0.6524 1.0000
1.250 0.5622 0.02629 0.01509 -0.0911 0.6455 1.0000
1.500 0.5839 0.02672 0.01540 -0.0902 0.6380 1.0000
1.750 0.6152 0.02677 0.01526 -0.0904 0.6330 1.0000
2.000 0.6287 0.02758 0.01604 -0.0886 0.6236 1.0000
2.250 0.6597 0.02766 0.01596 -0.0888 0.6184 1.0000
2.500 0.6731 0.02851 0.01678 -0.0870 0.6092 1.0000
2.750 0.7018 0.02870 0.01687 -0.0869 0.6035 1.0000
3.000 0.7170 0.02950 0.01765 -0.0853 0.5950 1.0000
3.250 0.7426 0.02983 0.01789 -0.0849 0.5885 1.0000
3.500 0.7605 0.03053 0.01859 -0.0836 0.5808 1.0000
3.750 0.7815 0.03107 0.01909 -0.0827 0.5734 1.0000
4.000 0.8041 0.03155 0.01954 -0.0819 0.5667 1.0000
4.250 0.8187 0.03240 0.02040 -0.0804 0.5583 1.0000
4.500 0.8527 0.03234 0.02028 -0.0808 0.5538 1.0000
4.750 0.8535 0.03386 0.02188 -0.0778 0.5431 1.0000
5.000 0.8871 0.03377 0.02175 -0.0782 0.5386 1.0000
5.500 0.9181 0.03541 0.02346 -0.0752 0.5235 1.0000
5.750 0.9133 0.03730 0.02544 -0.0719 0.5129 1.0000
6.000 0.9459 0.03721 0.02535 -0.0721 0.5085 1.0000
6.250 0.9362 0.03942 0.02763 -0.0684 0.4979 1.0000
6.500 0.9682 0.03936 0.02761 -0.0685 0.4936 1.0000
6.750 0.9505 0.04200 0.03032 -0.0643 0.4828 1.0000
7.000 0.9822 0.04191 0.03026 -0.0643 0.4787 1.0000
7.250 0.9601 0.04527 0.03368 -0.0605 0.4675 1.0000
7.500 0.9908 0.04513 0.03359 -0.0603 0.4637 1.0000
8.000 0.9962 0.04907 0.03768 -0.0570 0.4485 1.0000
8.500 0.9986 0.05382 0.04256 -0.0546 0.4332 1.0000
9.000 0.9981 0.05944 0.04832 -0.0529 0.4179 1.0000
9.500 0.9966 0.06569 0.05474 -0.0519 0.4026 1.0000
9.750 0.9684 0.07239 0.06147 -0.0522 0.3907 1.0000
10.000 0.9922 0.07266 0.06187 -0.0515 0.3877 1.0000
10.500 0.9848 0.08020 0.06957 -0.0514 0.3731 1.0000
10.750 1.0110 0.08024 0.06972 -0.0507 0.3709 1.0000
11.000 0.9766 0.08807 0.07760 -0.0518 0.3591 1.0000
11.250 1.0013 0.08828 0.07795 -0.0511 0.3564 1.0000
11.500 0.9700 0.09598 0.08569 -0.0526 0.3461 1.0000
11.750 0.9885 0.09704 0.08690 -0.0521 0.3424 1.0000
12.250 0.9824 0.10493 0.09499 -0.0531 0.3288 1.0000
12.500 1.0125 0.10407 0.09430 -0.0518 0.3256 1.0000
13.000 1.0262 0.10824 0.09874 -0.0514 0.3103 1.0000
13.250 1.0078 0.11394 0.10448 -0.0528 0.2985 1.0000
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Polar data table (+)
Polar graphs
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