GOE 404 AIRFOIL (goe404-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 404 AIRFOIL (goe404-il) Reynolds number: 50,000 Max Cl/Cd: 31.56 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe404-il-50000-n5.txt Download as CSV file: xf-goe404-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 404 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2651 0.10374 0.09722 -0.0276 1.0000 0.1295
-7.500 -0.2776 0.10262 0.09624 -0.0248 1.0000 0.1300
-7.250 -0.2815 0.10075 0.09446 -0.0243 0.9963 0.1308
-7.000 -0.2607 0.09670 0.09040 -0.0298 0.9841 0.1321
-6.750 -0.2377 0.09243 0.08612 -0.0362 0.9709 0.1335
-6.250 -0.2003 0.07715 0.07045 -0.0599 0.9394 0.0899
-6.000 -0.1754 0.07307 0.06631 -0.0642 0.9264 0.0886
-5.750 -0.1502 0.06858 0.06171 -0.0694 0.9141 0.0871
-5.500 -0.1254 0.06393 0.05689 -0.0747 0.9017 0.0858
-5.250 -0.1060 0.05991 0.05268 -0.0780 0.8869 0.0853
-5.000 -0.0838 0.05631 0.04886 -0.0809 0.8736 0.0863
-4.750 -0.0564 0.05243 0.04467 -0.0843 0.8631 0.0879
-4.500 -0.0366 0.04908 0.04099 -0.0857 0.8486 0.0890
-4.250 -0.0134 0.04572 0.03720 -0.0870 0.8359 0.0898
-4.000 0.0152 0.04263 0.03370 -0.0884 0.8258 0.0913
-3.750 0.0378 0.04131 0.03232 -0.0880 0.8118 0.0939
-3.500 0.0637 0.03936 0.03005 -0.0882 0.7995 0.0977
-3.250 0.0937 0.03669 0.02673 -0.0888 0.7893 0.1016
-3.000 0.1179 0.03566 0.02569 -0.0883 0.7756 0.1051
-2.750 0.1460 0.03417 0.02380 -0.0881 0.7640 0.1113
-2.500 0.1748 0.03290 0.02235 -0.0880 0.7526 0.1172
-2.250 0.2013 0.03192 0.02105 -0.0875 0.7392 0.1249
-2.000 0.2298 0.03098 0.01998 -0.0872 0.7276 0.1324
-1.750 0.2585 0.03020 0.01881 -0.0868 0.7152 0.1417
-1.500 0.2844 0.02955 0.01820 -0.0862 0.7020 0.1489
-1.250 0.3150 0.02888 0.01715 -0.0859 0.6910 0.1574
-1.000 0.3410 0.02835 0.01663 -0.0853 0.6771 0.1636
-0.750 0.3683 0.02796 0.01607 -0.0847 0.6646 0.1708
-0.500 0.3982 0.02749 0.01542 -0.0843 0.6535 0.1774
-0.250 0.4244 0.02727 0.01515 -0.0838 0.6401 0.1838
0.000 0.4532 0.02704 0.01472 -0.0833 0.6293 0.1919
0.250 0.4793 0.02681 0.01450 -0.0827 0.6174 0.1989
0.500 0.5055 0.02673 0.01432 -0.0821 0.6064 0.2081
0.750 0.5321 0.02651 0.01412 -0.0815 0.5963 0.2193
1.000 0.5567 0.02649 0.01411 -0.0809 0.5856 0.2321
1.250 0.5835 0.02629 0.01396 -0.0804 0.5768 0.2532
1.500 0.6075 0.02611 0.01412 -0.0800 0.5671 0.3022
1.750 0.6454 0.02451 0.01410 -0.0809 0.5585 1.0000
2.000 0.6696 0.02498 0.01432 -0.0801 0.5498 1.0000
2.250 0.6946 0.02538 0.01450 -0.0794 0.5416 1.0000
2.500 0.7203 0.02577 0.01468 -0.0788 0.5346 1.0000
2.750 0.7430 0.02636 0.01518 -0.0781 0.5265 1.0000
3.000 0.7697 0.02672 0.01536 -0.0776 0.5206 1.0000
3.250 0.7919 0.02738 0.01595 -0.0768 0.5134 1.0000
3.500 0.8155 0.02793 0.01643 -0.0762 0.5065 1.0000
3.750 0.8430 0.02826 0.01660 -0.0758 0.5014 1.0000
4.000 0.8624 0.02915 0.01751 -0.0749 0.4943 1.0000
4.250 0.8855 0.02980 0.01813 -0.0742 0.4884 1.0000
4.500 0.9128 0.03018 0.01838 -0.0738 0.4836 1.0000
4.750 0.9307 0.03113 0.01938 -0.0728 0.4764 1.0000
5.000 0.9533 0.03171 0.01993 -0.0719 0.4695 1.0000
5.250 0.9816 0.03189 0.01997 -0.0715 0.4636 1.0000
5.500 0.9954 0.03295 0.02113 -0.0700 0.4545 1.0000
5.750 1.0242 0.03294 0.02098 -0.0695 0.4472 1.0000
6.000 1.0380 0.03389 0.02201 -0.0678 0.4375 1.0000
6.250 1.0644 0.03401 0.02202 -0.0671 0.4297 1.0000
6.500 1.0798 0.03493 0.02302 -0.0657 0.4215 1.0000
6.750 1.0996 0.03560 0.02370 -0.0646 0.4143 1.0000
7.000 1.1285 0.03576 0.02375 -0.0643 0.4086 1.0000
7.250 1.1338 0.03733 0.02554 -0.0621 0.4001 1.0000
7.500 1.1576 0.03773 0.02591 -0.0613 0.3934 1.0000
7.750 1.1720 0.03873 0.02699 -0.0598 0.3863 1.0000
8.000 1.1825 0.03991 0.02828 -0.0580 0.3783 1.0000
8.250 1.2139 0.03979 0.02806 -0.0578 0.3721 1.0000
8.500 1.2060 0.04205 0.03058 -0.0546 0.3630 1.0000
8.750 1.2289 0.04235 0.03085 -0.0537 0.3560 1.0000
9.000 1.2275 0.04416 0.03281 -0.0510 0.3480 1.0000
9.250 1.2327 0.04548 0.03422 -0.0488 0.3402 1.0000
9.500 1.2506 0.04605 0.03478 -0.0476 0.3334 1.0000
9.750 1.2275 0.04955 0.03848 -0.0444 0.3242 1.0000
10.000 1.2646 0.04861 0.03745 -0.0439 0.3181 1.0000
10.250 1.2110 0.05531 0.04443 -0.0413 0.3075 1.0000
10.500 1.2444 0.05435 0.04342 -0.0402 0.3019 1.0000
10.750 1.1777 0.06416 0.05348 -0.0403 0.2897 1.0000
11.000 1.2109 0.06289 0.05219 -0.0388 0.2855 1.0000
11.250 1.1336 0.07623 0.06573 -0.0418 0.2717 1.0000
11.500 1.1662 0.07464 0.06415 -0.0400 0.2690 1.0000
12.000 1.1079 0.09034 0.07997 -0.0438 0.2516 1.0000
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Polar data table (+)
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