GOE 114 (MVA MK.1) AIRFOIL (goe114-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 114 (MVA MK.1) AIRFOIL (goe114-il) Reynolds number: 1,000,000 Max Cl/Cd: 70.58 at α=1° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe114-il-1000000.txt Download as CSV file: xf-goe114-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3790 0.10969 0.10805 -0.0370 1.0000 0.0041
-10.250 -0.3769 0.10562 0.10400 -0.0382 1.0000 0.0041
-10.000 -0.3742 0.10210 0.10048 -0.0392 1.0000 0.0041
-7.500 -0.3411 0.03733 0.03519 -0.1010 0.9648 0.0045
-7.250 -0.3208 0.03332 0.03097 -0.1054 0.9539 0.0049
-7.000 -0.3012 0.03098 0.02842 -0.1071 0.9406 0.0054
-6.750 -0.2843 0.02859 0.02577 -0.1072 0.9254 0.0058
-6.500 -0.2644 0.02713 0.02408 -0.1068 0.9118 0.0071
-6.250 -0.2374 0.02739 0.02418 -0.1062 0.9004 0.0085
-6.000 -0.2152 0.02685 0.02338 -0.1054 0.8885 0.0089
-5.750 -0.1961 0.02496 0.02121 -0.1046 0.8774 0.0089
-5.500 -0.1760 0.02299 0.01896 -0.1038 0.8675 0.0090
-5.250 -0.1546 0.02114 0.01683 -0.1031 0.8588 0.0090
-5.000 -0.1323 0.01934 0.01477 -0.1023 0.8505 0.0090
-4.750 -0.1089 0.01765 0.01283 -0.1016 0.8427 0.0090
-4.250 -0.0598 0.01467 0.00947 -0.1004 0.8282 0.0090
-4.000 -0.0382 0.01128 0.00597 -0.0991 0.8218 0.0079
-3.750 -0.0143 0.01003 0.00464 -0.0981 0.8149 0.0073
-3.500 0.0107 0.00931 0.00379 -0.0975 0.8087 0.0080
-3.250 0.0379 0.00912 0.00356 -0.0973 0.8021 0.0093
-3.000 0.0622 0.00821 0.00244 -0.0967 0.7960 0.0117
-2.750 0.0891 0.00787 0.00199 -0.0965 0.7897 0.0127
-2.500 0.1161 0.00761 0.00161 -0.0963 0.7836 0.0142
-2.250 0.1435 0.00745 0.00135 -0.0962 0.7775 0.0175
-2.000 0.1708 0.00736 0.00118 -0.0961 0.7713 0.0249
-1.750 0.1935 0.00629 0.00096 -0.0957 0.7654 0.2894
-1.500 0.2210 0.00630 0.00094 -0.0957 0.7590 0.3065
-1.250 0.2485 0.00629 0.00094 -0.0957 0.7527 0.3148
-1.000 0.2760 0.00631 0.00095 -0.0957 0.7453 0.3260
-0.750 0.3035 0.00635 0.00096 -0.0957 0.7373 0.3340
-0.250 0.3579 0.00635 0.00094 -0.0955 0.7199 0.3417
0.000 0.3850 0.00637 0.00093 -0.0955 0.7097 0.3449
0.250 0.4107 0.00643 0.00090 -0.0950 0.6873 0.3478
0.500 0.4365 0.00648 0.00090 -0.0947 0.6642 0.3515
0.750 0.4618 0.00659 0.00093 -0.0942 0.6360 0.3553
1.000 0.4849 0.00687 0.00099 -0.0934 0.5808 0.3586
1.250 0.5002 0.00777 0.00122 -0.0912 0.4328 0.3619
1.500 0.5047 0.00983 0.00199 -0.0874 0.1059 0.3650
1.750 0.5279 0.01026 0.00223 -0.0866 0.0193 0.3697
2.000 0.5539 0.01041 0.00242 -0.0863 0.0150 0.3741
2.250 0.5794 0.01058 0.00270 -0.0859 0.0136 0.3788
2.500 0.6032 0.01095 0.00321 -0.0851 0.0108 0.3833
2.750 0.6280 0.01121 0.00351 -0.0845 0.0089 0.3878
3.000 0.6507 0.01165 0.00407 -0.0834 0.0082 0.3929
3.250 0.6711 0.01232 0.00485 -0.0818 0.0084 0.3981
3.500 0.6876 0.01330 0.00594 -0.0795 0.0094 0.4032
4.750 0.8017 0.02017 0.01329 -0.0742 0.0102 0.5068
5.000 0.8339 0.01881 0.01314 -0.0753 0.0090 1.0000
5.250 0.8557 0.01891 0.01327 -0.0744 0.0062 1.0000
5.500 0.8810 0.02064 0.01495 -0.0744 0.0052 1.0000
5.750 0.8856 0.01507 0.00992 -0.0703 0.0046 1.0000
6.000 0.9046 0.01728 0.01235 -0.0685 0.0046 1.0000
6.250 0.9218 0.01970 0.01499 -0.0666 0.0046 1.0000
6.500 0.9373 0.02230 0.01784 -0.0645 0.0046 1.0000
6.750 0.9511 0.02512 0.02089 -0.0622 0.0045 1.0000
7.000 0.9631 0.02810 0.02408 -0.0599 0.0045 1.0000
7.250 0.9732 0.03126 0.02745 -0.0573 0.0045 1.0000
7.500 0.9813 0.03454 0.03095 -0.0547 0.0045 1.0000
7.750 0.9871 0.03789 0.03450 -0.0518 0.0045 1.0000
8.000 0.9911 0.04127 0.03807 -0.0490 0.0045 1.0000
8.250 0.9924 0.04463 0.04161 -0.0459 0.0044 1.0000
8.500 0.9911 0.04790 0.04505 -0.0428 0.0044 1.0000
8.750 0.9871 0.05102 0.04833 -0.0395 0.0044 1.0000
9.000 0.9782 0.05381 0.05127 -0.0357 0.0043 1.0000
9.250 0.9633 0.05628 0.05385 -0.0314 0.0043 1.0000
9.500 0.9460 0.05916 0.05685 -0.0280 0.0043 1.0000
9.750 0.9266 0.06261 0.06042 -0.0256 0.0042 1.0000
10.000 0.9049 0.06676 0.06469 -0.0241 0.0043 1.0000
10.250 0.8798 0.07186 0.06990 -0.0238 0.0043 1.0000
10.500 0.8549 0.07752 0.07567 -0.0245 0.0044 1.0000
10.750 0.8314 0.08351 0.08177 -0.0261 0.0044 1.0000
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Polar data table (+)
Polar graphs
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