GOE 360 AIRFOIL (goe360-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 360 AIRFOIL (goe360-il) Reynolds number: 50,000 Max Cl/Cd: 36.21 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe360-il-50000-n5.txt Download as CSV file: xf-goe360-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 360 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 -0.2740 0.10496 0.09902 -0.0287 1.0000 0.0771
-7.500 -0.2912 0.10485 0.09906 -0.0268 1.0000 0.0779
-7.250 -0.3048 0.10471 0.09905 -0.0270 0.9991 0.0786
-6.750 -0.2617 0.09472 0.08905 -0.0333 0.9831 0.0850
-6.500 -0.2366 0.09095 0.08523 -0.0407 0.9717 0.0906
-6.250 -0.2025 0.08840 0.08252 -0.0562 0.9560 0.0943
-6.000 -0.1845 0.08265 0.07682 -0.0539 0.9504 0.0976
-5.750 -0.1578 0.07903 0.07313 -0.0591 0.9398 0.1049
-5.250 -0.0902 0.07220 0.06598 -0.0759 0.9188 0.1243
-5.000 -0.0735 0.06798 0.06181 -0.0746 0.9089 0.1298
-4.500 -0.0125 0.06172 0.05525 -0.0848 0.8878 0.1563
-4.250 0.0097 0.05893 0.05237 -0.0866 0.8754 0.1722
-4.000 0.0288 0.05612 0.04957 -0.0867 0.8637 0.1916
-3.750 0.0493 0.05360 0.04698 -0.0874 0.8524 0.2225
-3.500 0.0689 0.05107 0.04444 -0.0873 0.8425 0.2672
-2.500 0.2342 0.04211 0.03333 -0.1023 0.7975 0.1238
-2.250 0.2568 0.03943 0.03066 -0.1021 0.7854 0.1160
-2.000 0.2885 0.03766 0.02849 -0.1026 0.7743 0.1014
-1.750 0.3229 0.03607 0.02638 -0.1030 0.7651 0.0911
-1.500 0.3507 0.03457 0.02462 -0.1029 0.7535 0.0872
-1.250 0.3798 0.03333 0.02301 -0.1027 0.7420 0.0834
-1.000 0.4114 0.03251 0.02166 -0.1023 0.7318 0.0798
-0.750 0.4408 0.03154 0.02036 -0.1020 0.7215 0.0795
-0.500 0.4670 0.03034 0.01906 -0.1018 0.7097 0.0814
-0.250 0.4949 0.02948 0.01800 -0.1014 0.6988 0.0827
0.000 0.5247 0.02864 0.01685 -0.1010 0.6895 0.0823
0.250 0.5511 0.02811 0.01611 -0.1002 0.6775 0.0820
0.500 0.5792 0.02761 0.01537 -0.0996 0.6663 0.0820
0.750 0.6080 0.02706 0.01461 -0.0991 0.6562 0.0826
1.000 0.6351 0.02666 0.01406 -0.0984 0.6452 0.0836
1.250 0.6606 0.02643 0.01373 -0.0977 0.6338 0.0861
1.500 0.6870 0.02623 0.01337 -0.0971 0.6234 0.0911
1.750 0.7135 0.02605 0.01306 -0.0965 0.6130 0.0954
2.000 0.7382 0.02604 0.01300 -0.0960 0.6015 0.0991
2.250 0.7645 0.02605 0.01289 -0.0955 0.5914 0.1042
2.500 0.7909 0.02606 0.01282 -0.0951 0.5814 0.1118
2.750 0.8154 0.02621 0.01304 -0.0946 0.5702 0.1308
3.000 0.8398 0.02471 0.01312 -0.0938 0.5614 1.0000
3.250 0.8645 0.02515 0.01332 -0.0931 0.5513 1.0000
3.500 0.8882 0.02565 0.01365 -0.0925 0.5413 1.0000
3.750 0.9147 0.02595 0.01374 -0.0921 0.5333 1.0000
4.000 0.9367 0.02659 0.01435 -0.0914 0.5232 1.0000
4.250 0.9621 0.02699 0.01463 -0.0910 0.5154 1.0000
4.500 0.9849 0.02759 0.01520 -0.0904 0.5064 1.0000
4.750 1.0090 0.02811 0.01566 -0.0899 0.4988 1.0000
5.000 1.0322 0.02870 0.01627 -0.0894 0.4909 1.0000
5.250 1.0560 0.02927 0.01682 -0.0889 0.4838 1.0000
5.500 1.0783 0.02995 0.01753 -0.0883 0.4763 1.0000
5.750 1.1032 0.03047 0.01806 -0.0879 0.4703 1.0000
6.000 1.1229 0.03139 0.01909 -0.0872 0.4628 1.0000
6.250 1.1492 0.03183 0.01951 -0.0869 0.4576 1.0000
6.500 1.1664 0.03297 0.02083 -0.0861 0.4503 1.0000
6.750 1.1896 0.03365 0.02157 -0.0856 0.4446 1.0000
7.000 1.2116 0.03447 0.02248 -0.0850 0.4393 1.0000
7.250 1.2274 0.03577 0.02397 -0.0841 0.4329 1.0000
7.500 1.2517 0.03642 0.02471 -0.0837 0.4282 1.0000
7.750 1.2673 0.03774 0.02622 -0.0827 0.4225 1.0000
8.000 1.2817 0.03915 0.02782 -0.0816 0.4167 1.0000
8.250 1.3057 0.03988 0.02867 -0.0812 0.4127 1.0000
8.500 1.3158 0.04167 0.03071 -0.0799 0.4074 1.0000
8.750 1.3228 0.04362 0.03290 -0.0783 0.4016 1.0000
9.000 1.3457 0.04442 0.03384 -0.0778 0.3976 1.0000
9.250 1.3499 0.04665 0.03630 -0.0761 0.3926 1.0000
9.500 1.3370 0.05015 0.04004 -0.0735 0.3865 1.0000
9.750 1.3565 0.05119 0.04126 -0.0728 0.3826 1.0000
10.000 1.3197 0.05657 0.04678 -0.0694 0.3760 1.0000
10.250 1.2833 0.06303 0.05334 -0.0679 0.3685 1.0000
10.500 1.3118 0.06306 0.05362 -0.0671 0.3658 1.0000
10.750 1.2148 0.07873 0.06918 -0.0692 0.3517 1.0000
11.000 1.2435 0.07811 0.06878 -0.0678 0.3497 1.0000
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Polar data table (+)
Polar graphs
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