GOE 439 AIRFOIL (goe439-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 439 AIRFOIL (goe439-il) Reynolds number: 50,000 Max Cl/Cd: 40.84 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe439-il-50000-n5.txt Download as CSV file: xf-goe439-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 439 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
------ -------- --------- --------- -------- -------- --------
-7.250 -0.2973 0.10095 0.09498 -0.0292 1.0000 0.0830
-7.000 -0.3068 0.10007 0.09426 -0.0296 1.0000 0.0837
-6.750 -0.3137 0.09894 0.09325 -0.0303 1.0000 0.0841
-6.500 -0.3189 0.09762 0.09203 -0.0316 1.0000 0.0843
-6.250 -0.3180 0.09340 0.08787 -0.0275 1.0000 0.0854
-6.000 -0.3180 0.09046 0.08500 -0.0239 1.0000 0.0877
-5.750 -0.3208 0.08845 0.08306 -0.0226 1.0000 0.0903
-5.500 -0.3195 0.08652 0.08118 -0.0241 0.9990 0.0948
-5.250 -0.2789 0.08196 0.07650 -0.0386 0.9879 0.0987
-5.000 -0.2597 0.07734 0.07190 -0.0384 0.9808 0.1024
-4.750 -0.2284 0.07300 0.06747 -0.0448 0.9717 0.1054
-4.500 -0.1725 0.06413 0.05818 -0.0606 0.9622 0.0579
-4.250 -0.1435 0.06002 0.05395 -0.0640 0.9535 0.0531
-4.000 -0.1066 0.05523 0.04896 -0.0702 0.9448 0.0509
-3.750 -0.0635 0.05044 0.04381 -0.0772 0.9373 0.0520
-3.500 -0.0223 0.04592 0.03888 -0.0829 0.9285 0.0537
-3.250 0.0172 0.04164 0.03413 -0.0874 0.9199 0.0541
-3.000 0.0626 0.03730 0.02910 -0.0922 0.9136 0.0551
-2.750 0.0954 0.03497 0.02645 -0.0942 0.9038 0.0612
-2.500 0.1387 0.03207 0.02289 -0.0974 0.8975 0.0668
-2.250 0.1742 0.02998 0.02025 -0.0988 0.8880 0.0748
-2.000 0.2123 0.02832 0.01806 -0.1005 0.8797 0.0863
-1.750 0.2507 0.02690 0.01616 -0.1019 0.8716 0.0984
-1.500 0.2822 0.02605 0.01512 -0.1024 0.8610 0.1152
-1.250 0.3203 0.02497 0.01368 -0.1036 0.8524 0.1296
-1.000 0.3559 0.02414 0.01270 -0.1046 0.8430 0.1560
-0.750 0.3869 0.02343 0.01197 -0.1049 0.8317 0.1876
-0.500 0.4186 0.02277 0.01139 -0.1054 0.8209 0.2399
-0.250 0.4522 0.02153 0.01093 -0.1064 0.8119 0.3965
0.000 0.4854 0.02024 0.01042 -0.1065 0.7999 1.0000
0.250 0.5146 0.02035 0.01014 -0.1063 0.7873 1.0000
0.500 0.5436 0.02046 0.00995 -0.1060 0.7746 1.0000
0.750 0.5726 0.02057 0.00980 -0.1058 0.7622 1.0000
1.000 0.6014 0.02067 0.00968 -0.1056 0.7496 1.0000
1.250 0.6304 0.02078 0.00959 -0.1053 0.7374 1.0000
1.500 0.6585 0.02091 0.00956 -0.1050 0.7247 1.0000
1.750 0.6845 0.02112 0.00964 -0.1043 0.7111 1.0000
2.000 0.7103 0.02134 0.00975 -0.1037 0.6973 1.0000
2.250 0.7359 0.02158 0.00992 -0.1031 0.6837 1.0000
2.500 0.7614 0.02183 0.01009 -0.1024 0.6701 1.0000
2.750 0.7868 0.02209 0.01029 -0.1017 0.6567 1.0000
3.000 0.8122 0.02235 0.01051 -0.1011 0.6434 1.0000
3.250 0.8376 0.02262 0.01077 -0.1004 0.6304 1.0000
3.500 0.8632 0.02289 0.01101 -0.0998 0.6176 1.0000
3.750 0.8892 0.02314 0.01125 -0.0992 0.6053 1.0000
4.000 0.9138 0.02348 0.01164 -0.0985 0.5924 1.0000
4.250 0.9379 0.02386 0.01207 -0.0977 0.5793 1.0000
4.500 0.9620 0.02427 0.01253 -0.0970 0.5667 1.0000
4.750 0.9863 0.02469 0.01300 -0.0963 0.5545 1.0000
5.000 1.0111 0.02511 0.01352 -0.0957 0.5429 1.0000
5.250 1.0370 0.02549 0.01395 -0.0951 0.5321 1.0000
5.500 1.0597 0.02605 0.01466 -0.0943 0.5200 1.0000
5.750 1.0825 0.02666 0.01542 -0.0935 0.5084 1.0000
6.000 1.1061 0.02724 0.01619 -0.0928 0.4977 1.0000
6.250 1.1320 0.02772 0.01679 -0.0923 0.4880 1.0000
6.500 1.1525 0.02852 0.01783 -0.0913 0.4767 1.0000
6.750 1.1743 0.02927 0.01882 -0.0905 0.4665 1.0000
7.000 1.1994 0.02987 0.01967 -0.0899 0.4574 1.0000
7.250 1.2192 0.03078 0.02090 -0.0888 0.4471 1.0000
7.500 1.2387 0.03129 0.02164 -0.0873 0.4326 1.0000
7.750 1.2524 0.03131 0.02178 -0.0844 0.4083 1.0000
8.000 1.2600 0.03138 0.02191 -0.0809 0.3782 1.0000
8.250 1.2666 0.03182 0.02245 -0.0775 0.3501 1.0000
8.500 1.2680 0.03253 0.02320 -0.0736 0.3150 1.0000
8.750 1.2662 0.03365 0.02430 -0.0697 0.2734 1.0000
9.000 1.2561 0.03549 0.02578 -0.0654 0.2048 1.0000
9.500 1.2189 0.04280 0.03179 -0.0591 0.0752 1.0000
9.750 1.2104 0.04627 0.03536 -0.0574 0.0578 1.0000
10.000 1.2024 0.04989 0.03903 -0.0563 0.0516 1.0000
10.250 1.1946 0.05370 0.04295 -0.0557 0.0480 1.0000
10.500 1.1867 0.05772 0.04711 -0.0555 0.0452 1.0000
10.750 1.1777 0.06206 0.05159 -0.0557 0.0431 1.0000
11.000 1.1676 0.06671 0.05636 -0.0562 0.0415 1.0000
11.250 1.1596 0.07123 0.06102 -0.0568 0.0397 1.0000
11.500 1.1536 0.07557 0.06555 -0.0573 0.0382 1.0000
11.750 1.1486 0.07978 0.06993 -0.0578 0.0369 1.0000
12.000 1.1448 0.08381 0.07410 -0.0582 0.0358 1.0000
12.250 1.1432 0.08747 0.07788 -0.0583 0.0348 1.0000
12.500 1.1434 0.09078 0.08126 -0.0580 0.0336 1.0000
12.750 1.1483 0.09319 0.08369 -0.0567 0.0319 1.0000
13.000 1.1571 0.09552 0.08631 -0.0558 0.0304 1.0000
13.250 1.1672 0.09779 0.08886 -0.0546 0.0289 1.0000
13.500 1.1796 0.09998 0.09134 -0.0531 0.0280 1.0000
13.750 1.1884 0.10301 0.09468 -0.0524 0.0274 1.0000
14.000 1.1912 0.10709 0.09907 -0.0528 0.0271 1.0000
14.250 1.1886 0.11204 0.10430 -0.0542 0.0269 1.0000
14.500 1.1822 0.11770 0.11023 -0.0565 0.0267 1.0000
14.750 1.1734 0.12395 0.11672 -0.0596 0.0267 1.0000
15.000 1.1630 0.13079 0.12379 -0.0633 0.0268 1.0000
15.250 1.1513 0.13828 0.13150 -0.0677 0.0270 1.0000
15.500 1.1390 0.14637 0.13978 -0.0727 0.0273 1.0000
15.750 1.1265 0.15510 0.14866 -0.0782 0.0277 1.0000
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Polar data table (+)
Polar graphs
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