GOE 114 (MVA MK.1) AIRFOIL (goe114-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 114 (MVA MK.1) AIRFOIL (goe114-il) Reynolds number: 100,000 Max Cl/Cd: 49.74 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe114-il-100000.txt Download as CSV file: xf-goe114-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 114 (MVA MK.1) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3941 0.10169 0.09716 -0.0409 1.0000 0.1325
-8.500 -0.3737 0.09726 0.09271 -0.0380 1.0000 0.1393
-8.250 -0.3923 0.09607 0.09167 -0.0393 1.0000 0.1455
-8.000 -0.3813 0.09226 0.08788 -0.0373 1.0000 0.1506
-7.750 -0.3898 0.09059 0.08632 -0.0362 1.0000 0.1575
-7.500 -0.3363 0.08009 0.07631 -0.0302 1.0000 0.1649
-7.250 -0.4050 0.08648 0.08241 -0.0314 1.0000 0.1656
-7.000 -0.4254 0.08581 0.08186 -0.0276 1.0000 0.1695
-6.750 -0.4724 0.08619 0.08243 -0.0291 1.0000 0.1731
-6.500 -0.4576 0.08262 0.07887 -0.0228 1.0000 0.1771
-6.250 -0.4669 0.08093 0.07725 -0.0210 1.0000 0.1833
-6.000 -0.4798 0.07848 0.07487 -0.0211 1.0000 0.1891
-5.750 -0.4789 0.07629 0.07271 -0.0186 1.0000 0.1939
-4.750 -0.4325 0.03740 0.03160 -0.0554 1.0000 0.0920
-4.500 -0.3954 0.03266 0.02565 -0.0566 0.9980 0.0673
-4.250 -0.3534 0.02990 0.02209 -0.0583 0.9937 0.0552
-4.000 -0.3171 0.02694 0.01878 -0.0596 0.9892 0.0496
-3.750 -0.2766 0.02547 0.01688 -0.0611 0.9842 0.0457
-3.500 -0.2407 0.02383 0.01525 -0.0627 0.9794 0.0502
-3.250 -0.2059 0.02282 0.01410 -0.0638 0.9732 0.0494
-3.000 -0.1652 0.02209 0.01315 -0.0662 0.9681 0.0504
-2.750 -0.1328 0.02150 0.01227 -0.0671 0.9605 0.0530
-2.500 -0.0900 0.02091 0.01147 -0.0700 0.9555 0.0648
-2.250 -0.0615 0.02025 0.01190 -0.0708 0.9474 0.3264
-2.000 -0.0238 0.02110 0.01246 -0.0725 0.9404 0.3850
-1.750 0.0061 0.02138 0.01269 -0.0731 0.9320 0.4188
-1.500 0.0323 0.02170 0.01327 -0.0728 0.9240 0.4838
-1.250 0.0706 0.02160 0.01300 -0.0752 0.9174 0.4952
-1.000 0.1006 0.02157 0.01288 -0.0760 0.9089 0.5077
-0.750 0.1425 0.02140 0.01260 -0.0789 0.9032 0.5211
-0.500 0.1708 0.02135 0.01254 -0.0794 0.8941 0.5302
-0.250 0.2161 0.02112 0.01229 -0.0829 0.8893 0.5408
0.000 0.2429 0.02112 0.01229 -0.0830 0.8795 0.5499
0.250 0.2873 0.02088 0.01210 -0.0862 0.8746 0.5629
0.500 0.3179 0.02084 0.01212 -0.0870 0.8655 0.5764
0.750 0.3573 0.02063 0.01204 -0.0893 0.8589 0.5945
1.000 0.3946 0.02035 0.01197 -0.0911 0.8517 0.6203
1.500 0.4894 0.01915 0.01188 -0.0985 0.8390 1.0000
1.750 0.5208 0.01928 0.01198 -0.0991 0.8301 1.0000
2.000 0.5639 0.01852 0.01123 -0.1005 0.8182 1.0000
2.250 0.6112 0.01630 0.00901 -0.0999 0.7903 1.0000
2.500 0.6427 0.01504 0.00782 -0.0977 0.7594 1.0000
2.750 0.6644 0.01402 0.00669 -0.0936 0.7067 1.0000
3.000 0.6789 0.01365 0.00590 -0.0889 0.6091 1.0000
3.250 0.6866 0.01456 0.00576 -0.0841 0.4368 1.0000
3.500 0.6782 0.01781 0.00695 -0.0786 0.0645 1.0000
3.750 0.6986 0.01861 0.00775 -0.0769 0.0534 1.0000
4.000 0.7191 0.01935 0.00870 -0.0752 0.0500 1.0000
4.250 0.7359 0.02039 0.00992 -0.0730 0.0458 1.0000
4.500 0.7477 0.02172 0.01151 -0.0702 0.0423 1.0000
4.750 0.7603 0.02291 0.01280 -0.0674 0.0422 1.0000
5.000 0.7732 0.02436 0.01423 -0.0647 0.0427 1.0000
5.250 0.7964 0.02588 0.01568 -0.0634 0.0439 1.0000
5.500 0.8256 0.02677 0.01672 -0.0626 0.0472 1.0000
5.750 0.8652 0.02895 0.01893 -0.0632 0.0529 1.0000
6.000 0.9075 0.03085 0.02103 -0.0634 0.0620 1.0000
6.250 0.9592 0.03504 0.02535 -0.0648 0.0788 1.0000
6.500 1.0126 0.03767 0.02867 -0.0639 0.1186 1.0000
10.500 0.8753 0.11799 0.11373 -0.0565 0.2338 1.0000
10.750 0.8741 0.12049 0.11628 -0.0552 0.2065 1.0000
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Polar data table (+)
Polar graphs
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