GOE 758 AIRFOIL (goe758-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 758 AIRFOIL (goe758-il) Reynolds number: 50,000 Max Cl/Cd: 25.8 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe758-il-50000-n5.txt Download as CSV file: xf-goe758-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 758 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.1984 0.09440 0.08845 -0.0534 0.9722 0.0918
-8.500 -0.3247 0.09516 0.08902 -0.0492 0.9890 0.0803
-8.250 -0.3066 0.09070 0.08455 -0.0535 0.9776 0.0796
-8.000 -0.2907 0.08622 0.08004 -0.0581 0.9651 0.0782
-7.750 -0.2787 0.08114 0.07494 -0.0640 0.9511 0.0763
-7.500 -0.2683 0.07438 0.06811 -0.0727 0.9365 0.0740
-7.250 -0.2677 0.06573 0.05921 -0.0828 0.9212 0.0711
-7.000 -0.2677 0.05791 0.05075 -0.0902 0.9063 0.0688
-6.750 -0.2481 0.05345 0.04588 -0.0939 0.8967 0.0688
-6.500 -0.2315 0.05011 0.04224 -0.0954 0.8844 0.0696
-6.250 -0.2111 0.04769 0.03965 -0.0962 0.8732 0.0707
-6.000 -0.1852 0.04466 0.03622 -0.0982 0.8653 0.0714
-5.750 -0.1683 0.04219 0.03332 -0.0980 0.8531 0.0713
-5.500 -0.1465 0.03992 0.03063 -0.0981 0.8431 0.0714
-5.250 -0.1204 0.03784 0.02815 -0.0985 0.8346 0.0719
-5.000 -0.0990 0.03629 0.02627 -0.0980 0.8244 0.0724
-4.750 -0.0698 0.03470 0.02436 -0.0984 0.8173 0.0737
-4.500 -0.0485 0.03369 0.02311 -0.0975 0.8071 0.0756
-4.250 -0.0180 0.03246 0.02155 -0.0979 0.8006 0.0783
-4.000 0.0040 0.03166 0.02048 -0.0969 0.7910 0.0800
-3.750 0.0339 0.03059 0.01927 -0.0970 0.7847 0.0817
-3.500 0.0556 0.02997 0.01859 -0.0960 0.7757 0.0837
-3.250 0.0836 0.02924 0.01774 -0.0958 0.7692 0.0866
-3.000 0.1071 0.02878 0.01713 -0.0950 0.7612 0.0901
-2.750 0.1339 0.02825 0.01647 -0.0947 0.7541 0.0959
-2.500 0.1601 0.02777 0.01591 -0.0945 0.7476 0.1053
-2.250 0.1828 0.02736 0.01548 -0.0937 0.7397 0.1178
-2.000 0.2131 0.02641 0.01468 -0.0941 0.7347 0.1553
-1.750 0.2298 0.02577 0.01475 -0.0930 0.7259 0.2984
-1.500 0.2511 0.02497 0.01483 -0.0914 0.7205 0.5122
-1.250 0.2645 0.02479 0.01514 -0.0880 0.7128 0.6572
-1.000 0.3405 0.02386 0.01482 -0.0942 0.7076 0.9544
-0.750 0.3846 0.02379 0.01432 -0.0975 0.7025 1.0000
-0.500 0.3983 0.02427 0.01457 -0.0957 0.6935 1.0000
-0.250 0.4263 0.02431 0.01429 -0.0957 0.6881 1.0000
0.000 0.4426 0.02482 0.01461 -0.0942 0.6795 1.0000
0.250 0.4698 0.02494 0.01448 -0.0939 0.6736 1.0000
0.500 0.4899 0.02538 0.01473 -0.0929 0.6659 1.0000
0.750 0.5145 0.02563 0.01479 -0.0923 0.6591 1.0000
1.000 0.5406 0.02587 0.01483 -0.0919 0.6530 1.0000
1.250 0.5597 0.02639 0.01524 -0.0908 0.6447 1.0000
1.500 0.5910 0.02642 0.01508 -0.0910 0.6397 1.0000
1.750 0.6051 0.02720 0.01579 -0.0892 0.6305 1.0000
2.000 0.6340 0.02735 0.01579 -0.0892 0.6248 1.0000
2.250 0.6514 0.02803 0.01641 -0.0878 0.6167 1.0000
2.500 0.6764 0.02836 0.01664 -0.0873 0.6099 1.0000
2.750 0.7002 0.02878 0.01697 -0.0867 0.6033 1.0000
3.000 0.7174 0.02948 0.01766 -0.0853 0.5950 1.0000
3.250 0.7501 0.02950 0.01756 -0.0856 0.5901 1.0000
3.500 0.7576 0.03066 0.01876 -0.0832 0.5801 1.0000
3.750 0.7878 0.03078 0.01881 -0.0833 0.5747 1.0000
4.000 0.7965 0.03192 0.01999 -0.0811 0.5652 1.0000
4.250 0.8241 0.03214 0.02016 -0.0808 0.5593 1.0000
4.500 0.8341 0.03324 0.02130 -0.0788 0.5504 1.0000
4.750 0.8577 0.03365 0.02171 -0.0781 0.5439 1.0000
5.000 0.8706 0.03462 0.02270 -0.0764 0.5359 1.0000
5.250 0.8889 0.03529 0.02339 -0.0752 0.5286 1.0000
5.500 0.9090 0.03589 0.02403 -0.0743 0.5221 1.0000
5.750 0.9161 0.03716 0.02535 -0.0720 0.5134 1.0000
6.000 0.9520 0.03690 0.02509 -0.0725 0.5094 1.0000
6.250 0.9384 0.03931 0.02758 -0.0685 0.4982 1.0000
6.500 0.9735 0.03907 0.02739 -0.0689 0.4943 1.0000
6.750 0.9519 0.04193 0.03032 -0.0643 0.4830 1.0000
7.000 0.9868 0.04166 0.03008 -0.0646 0.4792 1.0000
7.250 0.9612 0.04519 0.03367 -0.0604 0.4676 1.0000
7.500 0.9941 0.04490 0.03346 -0.0603 0.4640 1.0000
8.000 0.9977 0.04896 0.03765 -0.0569 0.4487 1.0000
8.500 0.9984 0.05386 0.04268 -0.0544 0.4331 1.0000
9.000 0.9970 0.05956 0.04853 -0.0528 0.4176 1.0000
10.000 0.9876 0.07328 0.06258 -0.0514 0.3871 1.0000
10.500 0.9802 0.08081 0.07027 -0.0514 0.3723 1.0000
10.750 1.0061 0.08088 0.07046 -0.0506 0.3700 1.0000
11.000 0.9706 0.08892 0.07854 -0.0519 0.3584 1.0000
11.250 0.9933 0.08941 0.07919 -0.0512 0.3554 1.0000
11.500 0.9669 0.09640 0.08623 -0.0525 0.3455 1.0000
11.750 0.9809 0.09813 0.08809 -0.0522 0.3414 1.0000
12.000 1.0064 0.09824 0.08836 -0.0514 0.3388 1.0000
12.250 0.9758 0.10587 0.09604 -0.0532 0.3280 1.0000
12.500 1.0006 0.10588 0.09621 -0.0523 0.3242 1.0000
13.500 1.0370 0.11251 0.10339 -0.0510 0.2928 1.0000
14.000 1.0314 0.11974 0.11085 -0.0524 0.2747 1.0000
14.500 1.0282 0.12681 0.11819 -0.0540 0.2560 1.0000
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Polar data table (+)
Polar graphs
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