GOE 117 (MVA MK.4) AIRFOIL (goe117-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 117 (MVA MK.4) AIRFOIL (goe117-il) Reynolds number: 50,000 Max Cl/Cd: 38.66 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe117-il-50000-n5.txt Download as CSV file: xf-goe117-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3391 0.10842 0.10182 -0.0396 1.0000 0.1132
-8.500 -0.3483 0.10666 0.10020 -0.0401 1.0000 0.1136
-8.000 -0.3621 0.09579 0.08952 -0.0429 1.0000 0.0592
-7.750 -0.3661 0.09298 0.08681 -0.0419 1.0000 0.0589
-7.500 -0.3683 0.09025 0.08416 -0.0405 1.0000 0.0584
-7.250 -0.3728 0.08765 0.08166 -0.0392 1.0000 0.0578
-7.000 -0.3784 0.08511 0.07920 -0.0381 1.0000 0.0570
-6.750 -0.3842 0.08243 0.07660 -0.0375 1.0000 0.0562
-6.500 -0.3891 0.07962 0.07386 -0.0372 1.0000 0.0554
-6.250 -0.3924 0.07649 0.07079 -0.0376 1.0000 0.0547
-6.000 -0.3805 0.07158 0.06583 -0.0424 0.9958 0.0537
-5.750 -0.3498 0.06456 0.05864 -0.0523 0.9864 0.0543
-5.500 -0.3167 0.05674 0.05051 -0.0625 0.9769 0.0560
-5.250 -0.2834 0.04866 0.04187 -0.0714 0.9674 0.0571
-5.000 -0.2498 0.04191 0.03434 -0.0777 0.9582 0.0579
-4.750 -0.2156 0.03753 0.02936 -0.0819 0.9500 0.0619
-4.500 -0.1809 0.03474 0.02611 -0.0847 0.9413 0.0676
-4.250 -0.1460 0.03148 0.02199 -0.0870 0.9326 0.0708
-4.000 -0.1077 0.02954 0.01968 -0.0897 0.9254 0.0793
-3.750 -0.0742 0.02782 0.01749 -0.0909 0.9154 0.0845
-3.500 -0.0365 0.02630 0.01561 -0.0927 0.9075 0.0893
-3.250 0.0006 0.02525 0.01434 -0.0944 0.8990 0.0972
-3.000 0.0362 0.02442 0.01337 -0.0958 0.8895 0.1105
-2.750 0.0772 0.02363 0.01254 -0.0982 0.8824 0.1562
-2.500 0.1083 0.02333 0.01234 -0.0989 0.8710 0.2194
-2.250 0.1393 0.02339 0.01228 -0.0996 0.8600 0.2725
-2.000 0.1700 0.02334 0.01220 -0.1002 0.8501 0.3284
-1.750 0.2038 0.02294 0.01166 -0.1012 0.8410 0.3574
-1.500 0.2332 0.02263 0.01124 -0.1015 0.8300 0.3759
-1.250 0.2633 0.02232 0.01088 -0.1018 0.8200 0.3999
-1.000 0.2955 0.02191 0.01049 -0.1025 0.8118 0.4320
-0.750 0.3208 0.02164 0.01034 -0.1021 0.8008 0.4747
-0.500 0.3454 0.02104 0.01019 -0.1014 0.7914 0.5702
-0.250 0.3921 0.02024 0.00984 -0.1043 0.7841 1.0000
0.000 0.4178 0.02052 0.00986 -0.1040 0.7739 1.0000
0.250 0.4473 0.02068 0.00979 -0.1043 0.7661 1.0000
0.500 0.4728 0.02097 0.00990 -0.1039 0.7567 1.0000
0.750 0.4985 0.02127 0.01004 -0.1037 0.7481 1.0000
1.000 0.5267 0.02148 0.01012 -0.1037 0.7408 1.0000
1.250 0.5503 0.02186 0.01042 -0.1032 0.7320 1.0000
1.500 0.5793 0.02205 0.01052 -0.1033 0.7257 1.0000
1.750 0.6016 0.02252 0.01094 -0.1026 0.7172 1.0000
2.000 0.6307 0.02271 0.01110 -0.1027 0.7112 1.0000
2.250 0.6523 0.02322 0.01162 -0.1019 0.7028 1.0000
2.500 0.6812 0.02344 0.01182 -0.1020 0.6972 1.0000
2.750 0.7024 0.02400 0.01242 -0.1012 0.6889 1.0000
3.000 0.7309 0.02424 0.01272 -0.1012 0.6832 1.0000
3.250 0.7520 0.02484 0.01340 -0.1003 0.6752 1.0000
3.500 0.7800 0.02512 0.01375 -0.1002 0.6693 1.0000
3.750 0.8009 0.02575 0.01453 -0.0994 0.6615 1.0000
4.000 0.8282 0.02608 0.01498 -0.0992 0.6554 1.0000
4.250 0.8489 0.02676 0.01581 -0.0983 0.6477 1.0000
4.500 0.8752 0.02718 0.01639 -0.0980 0.6414 1.0000
4.750 0.8959 0.02791 0.01736 -0.0971 0.6340 1.0000
5.000 0.9205 0.02846 0.01812 -0.0966 0.6275 1.0000
5.250 0.9417 0.02922 0.01913 -0.0958 0.6206 1.0000
5.500 0.9728 0.02900 0.01914 -0.0951 0.6094 1.0000
5.750 0.9997 0.02694 0.01708 -0.0910 0.5659 1.0000
6.000 1.0105 0.02644 0.01666 -0.0866 0.5264 1.0000
6.250 1.0190 0.02636 0.01674 -0.0823 0.4859 1.0000
6.500 1.0156 0.02652 0.01672 -0.0762 0.3804 1.0000
6.750 0.9914 0.02944 0.01771 -0.0692 0.1409 1.0000
7.000 0.9778 0.03246 0.02025 -0.0647 0.1049 1.0000
7.250 0.9728 0.03493 0.02272 -0.0614 0.0899 1.0000
7.500 0.9696 0.03734 0.02519 -0.0587 0.0783 1.0000
7.750 0.9668 0.03982 0.02776 -0.0564 0.0710 1.0000
8.000 0.9655 0.04229 0.03039 -0.0544 0.0660 1.0000
8.250 0.9632 0.04496 0.03319 -0.0526 0.0621 1.0000
8.500 0.9652 0.04732 0.03569 -0.0509 0.0578 1.0000
8.750 0.9707 0.04942 0.03792 -0.0493 0.0527 1.0000
9.000 0.9806 0.05122 0.03973 -0.0473 0.0491 1.0000
9.250 1.0233 0.05134 0.03999 -0.0445 0.0441 1.0000
9.500 1.1488 0.05405 0.04269 -0.0496 0.0363 1.0000
9.750 1.1708 0.05676 0.04602 -0.0485 0.0347 1.0000
10.000 1.1855 0.05972 0.04943 -0.0470 0.0330 1.0000
10.250 1.1958 0.06296 0.05306 -0.0453 0.0321 1.0000
10.500 1.2013 0.06636 0.05682 -0.0432 0.0318 1.0000
10.750 1.2007 0.06980 0.06061 -0.0409 0.0317 1.0000
11.000 1.1956 0.07322 0.06434 -0.0386 0.0317 1.0000
11.250 1.1865 0.07676 0.06818 -0.0366 0.0317 1.0000
11.500 1.1747 0.08045 0.07215 -0.0350 0.0318 1.0000
11.750 1.1606 0.08442 0.07638 -0.0339 0.0319 1.0000
12.000 1.1449 0.08868 0.08089 -0.0335 0.0321 1.0000
12.250 1.1275 0.09330 0.08573 -0.0338 0.0322 1.0000
12.500 1.1092 0.09831 0.09095 -0.0348 0.0324 1.0000
12.750 1.0900 0.10379 0.09663 -0.0366 0.0326 1.0000
13.000 1.0709 0.10972 0.10272 -0.0391 0.0329 1.0000
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Polar data table (+)
Polar graphs
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