GOE 425 AIRFOIL (goe425-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 425 AIRFOIL (goe425-il) Reynolds number: 50,000 Max Cl/Cd: 17.38 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe425-il-50000-n5.txt Download as CSV file: xf-goe425-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 425 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.2857 0.13256 0.12564 -0.0404 1.0000 0.1399
-11.250 -0.2905 0.12988 0.12305 -0.0429 1.0000 0.1405
-11.000 -0.2931 0.12689 0.12015 -0.0450 1.0000 0.1408
-10.000 -0.2852 0.10616 0.09966 -0.0527 0.9944 0.0870
-9.750 -0.2645 0.10187 0.09535 -0.0565 0.9722 0.0849
-9.500 -0.2529 0.09672 0.09018 -0.0617 0.9512 0.0824
-9.250 -0.2650 0.08757 0.08099 -0.0720 0.9303 0.0778
-9.000 -0.2531 0.08291 0.07628 -0.0763 0.9130 0.0769
-8.750 -0.2498 0.07724 0.07053 -0.0819 0.8956 0.0761
-8.500 -0.2578 0.07113 0.06431 -0.0880 0.8781 0.0753
-8.250 -0.2665 0.06583 0.05880 -0.0921 0.8629 0.0748
-8.000 -0.2717 0.06120 0.05390 -0.0948 0.8498 0.0746
-7.750 -0.2725 0.05722 0.04959 -0.0963 0.8376 0.0747
-7.500 -0.2694 0.05377 0.04579 -0.0969 0.8258 0.0748
-7.250 -0.2607 0.05051 0.04211 -0.0972 0.8167 0.0748
-7.000 -0.2506 0.04775 0.03897 -0.0970 0.8059 0.0747
-6.750 -0.2357 0.04515 0.03594 -0.0967 0.7976 0.0747
-6.500 -0.2198 0.04298 0.03338 -0.0962 0.7880 0.0749
-6.250 -0.1999 0.04090 0.03089 -0.0957 0.7808 0.0753
-6.000 -0.1810 0.03924 0.02889 -0.0951 0.7717 0.0759
-5.750 -0.1579 0.03761 0.02682 -0.0946 0.7652 0.0773
-5.500 -0.1368 0.03648 0.02547 -0.0940 0.7566 0.0788
-5.250 -0.1126 0.03546 0.02432 -0.0935 0.7497 0.0807
-5.000 -0.0884 0.03449 0.02317 -0.0930 0.7430 0.0823
-4.750 -0.0642 0.03362 0.02212 -0.0925 0.7356 0.0837
-4.500 -0.0372 0.03270 0.02099 -0.0921 0.7302 0.0855
-4.250 -0.0132 0.03209 0.02021 -0.0914 0.7232 0.0874
-4.000 0.0106 0.03154 0.01964 -0.0908 0.7166 0.0901
-3.750 0.0370 0.03097 0.01894 -0.0904 0.7118 0.0948
-3.500 0.0589 0.03070 0.01858 -0.0896 0.7048 0.0996
-3.250 0.0822 0.03028 0.01814 -0.0890 0.6990 0.1051
-3.000 0.1084 0.02977 0.01747 -0.0886 0.6945 0.1126
-2.750 0.1302 0.02946 0.01716 -0.0882 0.6883 0.1237
-2.500 0.1517 0.02894 0.01679 -0.0877 0.6823 0.1465
-2.250 0.1747 0.02784 0.01632 -0.0876 0.6780 0.2473
-2.000 0.1916 0.02735 0.01676 -0.0858 0.6732 0.4663
-1.750 0.2078 0.02768 0.01730 -0.0838 0.6669 0.5607
-1.500 0.2271 0.02773 0.01752 -0.0815 0.6622 0.6345
-1.250 0.2469 0.02758 0.01758 -0.0786 0.6588 0.7100
-1.000 0.2605 0.02797 0.01824 -0.0756 0.6524 0.7744
-0.750 0.2888 0.02813 0.01851 -0.0748 0.6473 0.8413
-0.500 0.3396 0.02817 0.01842 -0.0785 0.6435 0.9036
-0.250 0.3976 0.02834 0.01836 -0.0845 0.6394 0.9668
0.000 0.4258 0.02908 0.01894 -0.0867 0.6326 1.0000
0.250 0.4430 0.02949 0.01912 -0.0858 0.6281 1.0000
0.500 0.4673 0.02971 0.01910 -0.0854 0.6248 1.0000
0.750 0.4762 0.03085 0.02013 -0.0838 0.6179 1.0000
1.000 0.4946 0.03152 0.02065 -0.0829 0.6127 1.0000
1.250 0.5199 0.03184 0.02079 -0.0827 0.6091 1.0000
1.500 0.5376 0.03265 0.02148 -0.0818 0.6042 1.0000
1.750 0.5479 0.03390 0.02267 -0.0803 0.5974 1.0000
2.000 0.5721 0.03435 0.02298 -0.0799 0.5934 1.0000
2.250 0.6008 0.03456 0.02304 -0.0799 0.5906 1.0000
2.500 0.5984 0.03670 0.02520 -0.0776 0.5818 1.0000
2.750 0.6204 0.03733 0.02574 -0.0771 0.5774 1.0000
3.000 0.6486 0.03758 0.02588 -0.0770 0.5745 1.0000
3.500 0.6624 0.04093 0.02920 -0.0740 0.5609 1.0000
3.750 0.6904 0.04120 0.02940 -0.0739 0.5580 1.0000
4.250 0.6956 0.04531 0.03350 -0.0707 0.5435 1.0000
4.500 0.7242 0.04558 0.03372 -0.0706 0.5408 1.0000
5.500 0.7257 0.05570 0.04388 -0.0660 0.5115 1.0000
5.750 0.7457 0.05672 0.04490 -0.0656 0.5079 1.0000
6.000 0.7725 0.05716 0.04533 -0.0653 0.5055 1.0000
6.250 0.7493 0.06190 0.05011 -0.0641 0.4944 1.0000
6.500 0.7698 0.06291 0.05113 -0.0637 0.4907 1.0000
6.750 0.7950 0.06354 0.05178 -0.0634 0.4883 1.0000
7.000 0.7713 0.06849 0.05679 -0.0625 0.4781 1.0000
7.250 0.7896 0.06972 0.05804 -0.0621 0.4742 1.0000
7.500 0.8147 0.07036 0.05871 -0.0618 0.4717 1.0000
7.750 0.7940 0.07520 0.06360 -0.0612 0.4626 1.0000
8.000 0.8083 0.07683 0.06529 -0.0608 0.4582 1.0000
8.250 0.8323 0.07759 0.06610 -0.0605 0.4554 1.0000
8.750 0.8288 0.08387 0.07250 -0.0598 0.4424 1.0000
9.000 0.8521 0.08468 0.07338 -0.0594 0.4393 1.0000
9.250 0.8407 0.08860 0.07737 -0.0591 0.4305 1.0000
9.500 0.8609 0.08938 0.07821 -0.0585 0.4250 1.0000
10.000 0.8856 0.09185 0.08082 -0.0571 0.4093 1.0000
10.500 0.9058 0.09500 0.08414 -0.0560 0.3941 1.0000
10.750 0.9346 0.09466 0.08389 -0.0552 0.3904 1.0000
11.000 0.9228 0.09865 0.08797 -0.0551 0.3791 1.0000
11.250 0.9529 0.09803 0.08748 -0.0542 0.3754 1.0000
11.500 0.9416 0.10200 0.09154 -0.0542 0.3634 1.0000
11.750 0.9708 0.10129 0.09094 -0.0532 0.3593 1.0000
12.000 0.9619 0.10503 0.09478 -0.0533 0.3471 1.0000
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Polar data table (+)
Polar graphs
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