GOE 549 AIRFOIL (goe549-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 549 AIRFOIL (goe549-il) Reynolds number: 100,000 Max Cl/Cd: 52.81 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe549-il-100000-n5.txt Download as CSV file: xf-goe549-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2562 0.10876 0.10400 -0.0463 1.0000 0.0672
-9.750 -0.2576 0.10637 0.10170 -0.0457 1.0000 0.0678
-9.500 -0.2739 0.09696 0.09232 -0.0523 0.9922 0.0438
-9.250 -0.2597 0.09257 0.08792 -0.0562 0.9806 0.0435
-9.000 -0.2462 0.08817 0.08351 -0.0604 0.9685 0.0430
-8.750 -0.2354 0.08272 0.07807 -0.0664 0.9560 0.0430
-8.500 -0.2228 0.07718 0.07251 -0.0729 0.9438 0.0426
-8.250 -0.2120 0.07124 0.06655 -0.0800 0.9300 0.0420
-8.000 -0.2089 0.06387 0.05913 -0.0893 0.9123 0.0412
-7.750 -0.2129 0.05512 0.05015 -0.0987 0.8941 0.0401
-7.500 -0.2174 0.04856 0.04322 -0.1030 0.8772 0.0395
-7.250 -0.2149 0.04367 0.03790 -0.1046 0.8621 0.0393
-7.000 -0.2063 0.03973 0.03349 -0.1051 0.8484 0.0395
-6.750 -0.1925 0.03668 0.02999 -0.1051 0.8358 0.0406
-6.500 -0.1779 0.03405 0.02685 -0.1044 0.8225 0.0422
-6.250 -0.1608 0.03172 0.02398 -0.1036 0.8098 0.0433
-6.000 -0.1407 0.02974 0.02150 -0.1028 0.7981 0.0439
-5.750 -0.1185 0.02792 0.01936 -0.1023 0.7878 0.0452
-5.500 -0.0960 0.02676 0.01807 -0.1018 0.7762 0.0470
-5.250 -0.0723 0.02557 0.01664 -0.1012 0.7658 0.0483
-5.000 -0.0468 0.02436 0.01516 -0.1007 0.7571 0.0492
-4.750 -0.0225 0.02335 0.01395 -0.1001 0.7467 0.0501
-4.500 0.0032 0.02249 0.01289 -0.0995 0.7383 0.0518
-4.250 0.0287 0.02182 0.01200 -0.0990 0.7296 0.0537
-4.000 0.0534 0.02099 0.01113 -0.0984 0.7217 0.0551
-3.750 0.0782 0.02035 0.01043 -0.0978 0.7139 0.0564
-3.500 0.1031 0.01982 0.00984 -0.0972 0.7068 0.0579
-3.250 0.1280 0.01938 0.00929 -0.0966 0.6996 0.0597
-3.000 0.1535 0.01900 0.00877 -0.0960 0.6932 0.0619
-2.750 0.1785 0.01868 0.00837 -0.0955 0.6861 0.0652
-2.500 0.2047 0.01834 0.00796 -0.0951 0.6806 0.0713
-2.250 0.2296 0.01808 0.00768 -0.0946 0.6737 0.0795
-2.000 0.2555 0.01775 0.00736 -0.0941 0.6678 0.0998
-1.750 0.2803 0.01723 0.00706 -0.0937 0.6622 0.1656
-1.500 0.3036 0.01666 0.00702 -0.0932 0.6557 0.3152
-1.250 0.3285 0.01624 0.00702 -0.0927 0.6505 0.4444
-1.000 0.3517 0.01605 0.00713 -0.0916 0.6444 0.5564
-0.750 0.3752 0.01590 0.00718 -0.0904 0.6383 0.6423
-0.500 0.4004 0.01565 0.00714 -0.0892 0.6334 0.7348
-0.250 0.4612 0.01532 0.00718 -0.0948 0.6258 0.9259
0.000 0.5147 0.01539 0.00701 -0.1001 0.6195 1.0000
0.250 0.5374 0.01558 0.00704 -0.0993 0.6136 1.0000
0.500 0.5604 0.01577 0.00709 -0.0985 0.6073 1.0000
0.750 0.5858 0.01594 0.00707 -0.0980 0.6023 1.0000
1.000 0.6082 0.01616 0.00722 -0.0971 0.5959 1.0000
1.250 0.6324 0.01636 0.00730 -0.0965 0.5899 1.0000
1.500 0.6583 0.01655 0.00734 -0.0961 0.5850 1.0000
1.750 0.6803 0.01679 0.00756 -0.0952 0.5781 1.0000
2.000 0.7053 0.01698 0.00765 -0.0946 0.5725 1.0000
2.250 0.7297 0.01720 0.00780 -0.0940 0.5669 1.0000
2.500 0.7526 0.01744 0.00801 -0.0932 0.5602 1.0000
2.750 0.7784 0.01761 0.00809 -0.0928 0.5549 1.0000
3.000 0.8008 0.01788 0.00836 -0.0919 0.5482 1.0000
3.250 0.8249 0.01808 0.00853 -0.0913 0.5420 1.0000
3.500 0.8497 0.01828 0.00868 -0.0907 0.5363 1.0000
3.750 0.8717 0.01855 0.00897 -0.0898 0.5291 1.0000
4.000 0.8972 0.01871 0.00908 -0.0893 0.5236 1.0000
4.250 0.9186 0.01901 0.00942 -0.0883 0.5162 1.0000
4.500 0.9427 0.01921 0.00960 -0.0876 0.5100 1.0000
4.750 0.9654 0.01947 0.00989 -0.0868 0.5034 1.0000
5.000 0.9879 0.01972 0.01015 -0.0860 0.4963 1.0000
5.250 1.0118 0.01993 0.01035 -0.0853 0.4903 1.0000
5.500 1.0328 0.02025 0.01075 -0.0842 0.4827 1.0000
5.750 1.0576 0.02043 0.01088 -0.0837 0.4771 1.0000
6.000 1.0770 0.02083 0.01137 -0.0825 0.4691 1.0000
6.250 1.1006 0.02105 0.01158 -0.0818 0.4630 1.0000
6.500 1.1205 0.02144 0.01206 -0.0806 0.4557 1.0000
6.750 1.1427 0.02174 0.01237 -0.0797 0.4492 1.0000
7.000 1.1633 0.02211 0.01280 -0.0787 0.4426 1.0000
7.250 1.1836 0.02249 0.01322 -0.0776 0.4356 1.0000
7.500 1.2057 0.02283 0.01360 -0.0767 0.4298 1.0000
7.750 1.2236 0.02333 0.01420 -0.0753 0.4228 1.0000
8.000 1.2463 0.02365 0.01452 -0.0746 0.4173 1.0000
8.250 1.2622 0.02420 0.01519 -0.0730 0.4100 1.0000
8.500 1.2819 0.02458 0.01561 -0.0718 0.4033 1.0000
8.750 1.2978 0.02511 0.01624 -0.0701 0.3963 1.0000
9.000 1.3145 0.02557 0.01675 -0.0686 0.3891 1.0000
9.250 1.3296 0.02609 0.01734 -0.0668 0.3821 1.0000
9.500 1.3424 0.02665 0.01801 -0.0647 0.3753 1.0000
9.750 1.3600 0.02713 0.01851 -0.0633 0.3697 1.0000
10.000 1.3682 0.02791 0.01946 -0.0608 0.3634 1.0000
10.250 1.3836 0.02846 0.02005 -0.0592 0.3576 1.0000
10.500 1.3914 0.02928 0.02099 -0.0567 0.3508 1.0000
10.750 1.4005 0.03002 0.02183 -0.0545 0.3436 1.0000
11.000 1.4074 0.03091 0.02282 -0.0522 0.3362 1.0000
11.250 1.4124 0.03187 0.02385 -0.0499 0.3281 1.0000
11.500 1.4128 0.03313 0.02522 -0.0474 0.3190 1.0000
11.750 1.4174 0.03418 0.02627 -0.0453 0.3096 1.0000
12.000 1.4118 0.03605 0.02831 -0.0429 0.3000 1.0000
12.250 1.4099 0.03781 0.03015 -0.0410 0.2902 1.0000
12.500 1.4081 0.03964 0.03201 -0.0393 0.2799 1.0000
12.750 1.4005 0.04225 0.03479 -0.0378 0.2698 1.0000
13.000 1.3933 0.04499 0.03762 -0.0367 0.2588 1.0000
13.250 1.3858 0.04792 0.04062 -0.0358 0.2475 1.0000
13.500 1.3776 0.05109 0.04385 -0.0352 0.2359 1.0000
13.750 1.3670 0.05479 0.04765 -0.0349 0.2237 1.0000
14.000 1.3564 0.05867 0.05162 -0.0348 0.2111 1.0000
14.250 1.3456 0.06272 0.05573 -0.0349 0.1982 1.0000
14.500 1.3339 0.06701 0.06007 -0.0352 0.1842 1.0000
14.750 1.3216 0.07154 0.06462 -0.0357 0.1693 1.0000
15.000 1.3076 0.07643 0.06949 -0.0364 0.1536 1.0000
15.250 1.2926 0.08164 0.07467 -0.0374 0.1379 1.0000
15.500 1.2769 0.08715 0.08015 -0.0386 0.1236 1.0000
15.750 1.2614 0.09280 0.08578 -0.0401 0.1121 1.0000
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