GOE 419 AIRFOIL (goe419-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 419 AIRFOIL (goe419-il) Reynolds number: 500,000 Max Cl/Cd: 102.04 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe419-il-500000-n5.txt Download as CSV file: xf-goe419-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 419 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3661 0.09656 0.09438 -0.0217 1.0000 0.0045
-8.000 -0.3647 0.09393 0.09178 -0.0218 1.0000 0.0048
-7.750 -0.3645 0.09151 0.08940 -0.0216 1.0000 0.0051
-6.000 -0.2387 0.06284 0.06071 -0.0570 0.9610 0.0063
-5.750 -0.2156 0.05784 0.05565 -0.0623 0.9492 0.0066
-5.500 -0.1853 0.05343 0.05117 -0.0680 0.9412 0.0068
-5.250 -0.1492 0.04881 0.04644 -0.0746 0.9344 0.0071
-5.000 -0.1068 0.04369 0.04118 -0.0822 0.9292 0.0072
-4.750 -0.0627 0.03854 0.03582 -0.0891 0.9228 0.0055
-4.500 -0.0186 0.03295 0.02997 -0.0954 0.9150 0.0045
-4.000 0.0567 0.02066 0.01678 -0.1013 0.8921 0.0035
-3.750 0.0833 0.01459 0.00989 -0.1008 0.8805 0.0034
-3.500 0.1099 0.01207 0.00671 -0.1002 0.8696 0.0035
-3.250 0.1360 0.01045 0.00465 -0.0996 0.8593 0.0039
-3.000 0.1622 0.00981 0.00383 -0.0992 0.8489 0.0048
-2.750 0.1881 0.00935 0.00322 -0.0987 0.8380 0.0065
-2.500 0.2133 0.00869 0.00235 -0.0980 0.8274 0.0086
-2.250 0.2391 0.00833 0.00188 -0.0974 0.8177 0.0162
-2.000 0.2655 0.00823 0.00174 -0.0971 0.8083 0.0306
-1.750 0.2915 0.00813 0.00158 -0.0968 0.7985 0.0400
-1.500 0.3174 0.00798 0.00135 -0.0964 0.7883 0.0449
-1.250 0.3432 0.00789 0.00120 -0.0959 0.7766 0.0492
-1.000 0.3689 0.00780 0.00108 -0.0955 0.7637 0.0616
-0.750 0.3944 0.00772 0.00097 -0.0950 0.7488 0.0839
-0.500 0.4197 0.00764 0.00090 -0.0945 0.7317 0.1140
-0.250 0.4446 0.00758 0.00087 -0.0940 0.7125 0.1574
0.000 0.4691 0.00752 0.00087 -0.0934 0.6917 0.2157
0.250 0.4929 0.00738 0.00089 -0.0927 0.6719 0.3179
0.500 0.5455 0.00598 0.00100 -0.0988 0.6537 1.0000
0.750 0.5693 0.00611 0.00103 -0.0980 0.6389 1.0000
1.000 0.5935 0.00624 0.00109 -0.0973 0.6256 1.0000
1.250 0.6180 0.00636 0.00116 -0.0966 0.6138 1.0000
1.500 0.6425 0.00648 0.00124 -0.0960 0.6020 1.0000
1.750 0.6671 0.00660 0.00134 -0.0954 0.5902 1.0000
2.000 0.6908 0.00677 0.00148 -0.0946 0.5690 1.0000
2.250 0.7108 0.00712 0.00160 -0.0930 0.5070 1.0000
2.500 0.7260 0.00791 0.00186 -0.0906 0.4002 1.0000
2.750 0.7305 0.00994 0.00259 -0.0868 0.1287 1.0000
3.000 0.7478 0.01096 0.00323 -0.0849 0.0122 1.0000
3.250 0.7713 0.01132 0.00373 -0.0840 0.0088 1.0000
3.500 0.7936 0.01184 0.00436 -0.0829 0.0061 1.0000
3.750 0.8150 0.01247 0.00508 -0.0816 0.0052 1.0000
4.000 0.8351 0.01323 0.00592 -0.0800 0.0047 1.0000
4.250 0.8532 0.01418 0.00695 -0.0782 0.0039 1.0000
4.500 0.8736 0.01487 0.00775 -0.0767 0.0030 1.0000
4.750 0.8921 0.01584 0.00879 -0.0750 0.0026 1.0000
5.250 0.9276 0.01936 0.01247 -0.0710 0.0023 1.0000
5.750 0.9768 0.02314 0.01651 -0.0689 0.0024 1.0000
6.000 1.0055 0.02670 0.02040 -0.0672 0.0034 1.0000
8.000 1.1011 0.05260 0.04835 -0.0493 0.0042 1.0000
8.250 1.1023 0.05583 0.05184 -0.0464 0.0042 1.0000
8.500 1.1009 0.05898 0.05522 -0.0434 0.0041 1.0000
8.750 1.0961 0.06220 0.05866 -0.0403 0.0041 1.0000
9.000 1.0880 0.06525 0.06190 -0.0372 0.0041 1.0000
9.250 1.0735 0.06794 0.06474 -0.0333 0.0041 1.0000
9.500 1.0577 0.07076 0.06770 -0.0302 0.0041 1.0000
9.750 1.0408 0.07397 0.07104 -0.0284 0.0041 1.0000
10.000 1.0244 0.07764 0.07484 -0.0279 0.0041 1.0000
10.250 1.0073 0.08189 0.07921 -0.0285 0.0041 1.0000
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Polar data table (+)
Polar graphs
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