GOE 117 (MVA MK.4) AIRFOIL (goe117-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 117 (MVA MK.4) AIRFOIL (goe117-il) Reynolds number: 500,000 Max Cl/Cd: 107.84 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe117-il-500000.txt Download as CSV file: xf-goe117-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 117 (MVA MK.4) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
0.250 0.4826 0.00861 0.00177 -0.1018 0.6031 0.3428
0.500 0.5092 0.00855 0.00181 -0.1016 0.5977 0.3713
0.750 0.5353 0.00845 0.00187 -0.1014 0.5924 0.4243
1.000 0.5522 0.00759 0.00200 -0.0993 0.5877 0.7843
1.250 0.6103 0.00733 0.00207 -0.1058 0.5813 1.0000
1.500 0.6360 0.00744 0.00213 -0.1054 0.5762 1.0000
1.750 0.6620 0.00758 0.00222 -0.1050 0.5719 1.0000
2.000 0.6881 0.00766 0.00231 -0.1046 0.5675 1.0000
2.250 0.7141 0.00776 0.00239 -0.1043 0.5632 1.0000
2.500 0.7401 0.00793 0.00250 -0.1039 0.5584 1.0000
2.750 0.7656 0.00797 0.00259 -0.1034 0.5511 1.0000
3.000 0.7914 0.00811 0.00269 -0.1030 0.5454 1.0000
3.250 0.8167 0.00816 0.00278 -0.1025 0.5365 1.0000
3.500 0.8416 0.00827 0.00287 -0.1019 0.5269 1.0000
3.750 0.8663 0.00837 0.00296 -0.1012 0.5154 1.0000
4.000 0.8907 0.00844 0.00304 -0.1005 0.4999 1.0000
4.250 0.9151 0.00853 0.00313 -0.0998 0.4808 1.0000
4.500 0.9382 0.00870 0.00323 -0.0989 0.4501 1.0000
4.750 0.9514 0.00959 0.00357 -0.0963 0.3376 1.0000
5.000 0.9441 0.01249 0.00514 -0.0909 0.0700 1.0000
5.250 0.9623 0.01324 0.00576 -0.0892 0.0416 1.0000
5.500 0.9828 0.01378 0.00634 -0.0879 0.0344 1.0000
5.750 0.9989 0.01464 0.00726 -0.0859 0.0280 1.0000
6.000 1.0198 0.01508 0.00775 -0.0847 0.0257 1.0000
6.250 1.0382 0.01568 0.00841 -0.0830 0.0233 1.0000
6.500 1.0538 0.01643 0.00920 -0.0810 0.0215 1.0000
6.750 1.0559 0.01799 0.01089 -0.0767 0.0199 1.0000
7.000 1.0741 0.01846 0.01141 -0.0751 0.0188 1.0000
7.250 1.0870 0.01913 0.01213 -0.0726 0.0178 1.0000
7.500 1.0959 0.02002 0.01309 -0.0695 0.0170 1.0000
7.750 1.1059 0.02092 0.01405 -0.0667 0.0162 1.0000
8.000 1.1159 0.02191 0.01509 -0.0640 0.0156 1.0000
8.250 1.1262 0.02300 0.01623 -0.0615 0.0150 1.0000
8.500 1.1368 0.02456 0.01782 -0.0592 0.0144 1.0000
8.750 1.1679 0.02783 0.02120 -0.0600 0.0136 1.0000
9.000 1.1823 0.02853 0.02203 -0.0580 0.0131 1.0000
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Polar data table (+)
Polar graphs
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