GOE 240 (KOLLER) AIRFOIL (goe240-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 240 (KOLLER) AIRFOIL (goe240-il) Reynolds number: 100,000 Max Cl/Cd: 62.24 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe240-il-100000-n5.txt Download as CSV file: xf-goe240-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 240 (KOLLER) 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3053 0.09606 0.09148 -0.0265 1.0000 0.0398
-7.250 -0.3126 0.09474 0.09030 -0.0264 1.0000 0.0406
-7.000 -0.3181 0.09342 0.08908 -0.0276 1.0000 0.0411
-6.750 -0.3228 0.09199 0.08773 -0.0288 1.0000 0.0413
-6.500 -0.3006 0.08684 0.08257 -0.0351 0.9944 0.0421
-6.250 -0.2882 0.08294 0.07868 -0.0321 0.9908 0.0449
-6.000 -0.2576 0.07879 0.07448 -0.0400 0.9835 0.0496
-5.750 -0.2035 0.07358 0.06907 -0.0593 0.9729 0.0523
-5.500 -0.1918 0.06927 0.06482 -0.0569 0.9675 0.0539
-5.250 -0.1630 0.06563 0.06113 -0.0610 0.9610 0.0584
-5.000 -0.1149 0.06065 0.05592 -0.0733 0.9524 0.0645
-4.750 -0.0919 0.05716 0.05240 -0.0748 0.9440 0.0670
-4.500 -0.0560 0.05344 0.04854 -0.0802 0.9369 0.0710
-4.250 -0.0043 0.04974 0.04431 -0.0902 0.9264 0.0764
-3.750 0.0503 0.04122 0.03558 -0.0941 0.9117 0.0599
-3.500 0.0983 0.03549 0.02909 -0.0997 0.9065 0.0518
-3.250 0.1281 0.03265 0.02591 -0.1011 0.8977 0.0518
-3.000 0.1612 0.03000 0.02303 -0.1030 0.8923 0.0510
-2.750 0.1914 0.02772 0.02042 -0.1040 0.8841 0.0505
-2.500 0.2262 0.02551 0.01779 -0.1055 0.8787 0.0505
-2.250 0.2576 0.02382 0.01561 -0.1061 0.8708 0.0524
-2.000 0.2910 0.02225 0.01371 -0.1070 0.8651 0.0526
-1.750 0.3211 0.02102 0.01217 -0.1073 0.8571 0.0524
-1.500 0.3536 0.01985 0.01074 -0.1079 0.8510 0.0526
-1.250 0.3828 0.01897 0.00970 -0.1080 0.8425 0.0531
-0.750 0.4423 0.01759 0.00812 -0.1081 0.8264 0.0551
-0.500 0.4711 0.01708 0.00753 -0.1079 0.8162 0.0570
-0.250 0.4997 0.01671 0.00704 -0.1076 0.8046 0.0615
0.000 0.5277 0.01631 0.00659 -0.1072 0.7922 0.0651
0.250 0.5538 0.01604 0.00628 -0.1065 0.7793 0.0683
0.500 0.5804 0.01585 0.00601 -0.1059 0.7678 0.0735
0.750 0.6079 0.01566 0.00578 -0.1055 0.7572 0.0835
1.000 0.6357 0.01548 0.00555 -0.1051 0.7467 0.1070
1.250 0.6620 0.01518 0.00556 -0.1048 0.7344 0.2045
1.750 0.7145 0.01378 0.00557 -0.1038 0.7098 1.0000
2.000 0.7407 0.01391 0.00558 -0.1032 0.6968 1.0000
2.250 0.7667 0.01403 0.00562 -0.1026 0.6832 1.0000
2.500 0.7924 0.01416 0.00568 -0.1020 0.6682 1.0000
2.750 0.8177 0.01428 0.00573 -0.1013 0.6501 1.0000
3.000 0.8427 0.01439 0.00573 -0.1004 0.6293 1.0000
3.250 0.8672 0.01452 0.00577 -0.0995 0.6047 1.0000
3.500 0.8916 0.01469 0.00577 -0.0985 0.5788 1.0000
3.750 0.9157 0.01493 0.00583 -0.0975 0.5538 1.0000
4.000 0.9399 0.01523 0.00602 -0.0967 0.5315 1.0000
4.250 0.9642 0.01555 0.00627 -0.0959 0.5122 1.0000
4.500 0.9883 0.01591 0.00655 -0.0952 0.4932 1.0000
4.750 1.0121 0.01626 0.00688 -0.0944 0.4716 1.0000
5.000 1.0354 0.01664 0.00723 -0.0936 0.4483 1.0000
5.250 1.0584 0.01703 0.00758 -0.0927 0.4229 1.0000
5.500 1.0808 0.01746 0.00795 -0.0918 0.3973 1.0000
5.750 1.1027 0.01794 0.00835 -0.0908 0.3735 1.0000
6.000 1.1248 0.01844 0.00884 -0.0899 0.3521 1.0000
6.250 1.1463 0.01900 0.00935 -0.0889 0.3320 1.0000
6.500 1.1673 0.01959 0.00991 -0.0879 0.3131 1.0000
6.750 1.1886 0.02017 0.01051 -0.0869 0.2947 1.0000
7.000 1.2097 0.02076 0.01117 -0.0859 0.2773 1.0000
7.250 1.2302 0.02138 0.01183 -0.0849 0.2592 1.0000
7.500 1.2486 0.02212 0.01249 -0.0836 0.2325 1.0000
7.750 1.2657 0.02295 0.01321 -0.0822 0.2046 1.0000
8.000 1.2835 0.02375 0.01398 -0.0809 0.1868 1.0000
8.250 1.3001 0.02463 0.01487 -0.0795 0.1694 1.0000
8.500 1.3169 0.02549 0.01577 -0.0781 0.1550 1.0000
8.750 1.3325 0.02642 0.01673 -0.0765 0.1383 1.0000
9.000 1.3468 0.02749 0.01776 -0.0749 0.1071 1.0000
9.250 1.3505 0.02946 0.01930 -0.0721 0.0574 1.0000
9.500 1.3568 0.03107 0.02098 -0.0694 0.0447 1.0000
9.750 1.3636 0.03257 0.02265 -0.0667 0.0331 1.0000
10.250 1.3730 0.03597 0.02616 -0.0617 0.0235 1.0000
10.500 1.3755 0.03790 0.02820 -0.0593 0.0218 1.0000
10.750 1.3758 0.04007 0.03053 -0.0571 0.0208 1.0000
11.000 1.3732 0.04258 0.03324 -0.0550 0.0200 1.0000
11.250 1.3709 0.04519 0.03606 -0.0534 0.0196 1.0000
11.500 1.3674 0.04807 0.03916 -0.0521 0.0192 1.0000
11.750 1.3627 0.05123 0.04254 -0.0511 0.0189 1.0000
12.000 1.3568 0.05467 0.04619 -0.0504 0.0185 1.0000
12.250 1.3501 0.05835 0.05008 -0.0501 0.0180 1.0000
12.500 1.3429 0.06226 0.05417 -0.0500 0.0176 1.0000
12.750 1.3352 0.06639 0.05852 -0.0502 0.0172 1.0000
13.000 1.3274 0.07068 0.06300 -0.0507 0.0168 1.0000
13.250 1.3194 0.07513 0.06761 -0.0514 0.0164 1.0000
13.500 1.3118 0.07966 0.07230 -0.0522 0.0161 1.0000
13.750 1.3049 0.08417 0.07697 -0.0531 0.0158 1.0000
14.000 1.2989 0.08859 0.08154 -0.0539 0.0156 1.0000
14.250 1.2940 0.09291 0.08600 -0.0547 0.0154 1.0000
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Polar data table (+)
Polar graphs
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