GOE 116 (MVA MK.3) AIRFOIL (goe116-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 116 (MVA MK.3) AIRFOIL (goe116-il) Reynolds number: 100,000 Max Cl/Cd: 56.79 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe116-il-100000-n5.txt Download as CSV file: xf-goe116-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 116 (MVA MK.3) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3783 0.09203 0.08756 -0.0378 1.0000 0.0214
-8.500 -0.3782 0.08799 0.08360 -0.0397 1.0000 0.0209
-8.250 -0.3802 0.08394 0.07965 -0.0414 1.0000 0.0204
-8.000 -0.3857 0.08017 0.07600 -0.0427 1.0000 0.0200
-7.750 -0.3962 0.07685 0.07284 -0.0432 1.0000 0.0197
-7.500 -0.3869 0.06949 0.06551 -0.0524 0.9835 0.0190
-7.250 -0.3711 0.05711 0.05303 -0.0690 0.9624 0.0180
-7.000 -0.3489 0.04145 0.03655 -0.0879 0.9439 0.0169
-6.750 -0.3225 0.03559 0.02995 -0.0934 0.9309 0.0165
-6.500 -0.2949 0.03182 0.02556 -0.0961 0.9193 0.0164
-6.250 -0.2666 0.02900 0.02223 -0.0977 0.9087 0.0164
-6.000 -0.2384 0.02678 0.01961 -0.0986 0.8986 0.0167
-5.750 -0.2118 0.02499 0.01752 -0.0991 0.8878 0.0180
-5.500 -0.1844 0.02355 0.01573 -0.0995 0.8782 0.0196
-5.250 -0.1563 0.02238 0.01425 -0.0997 0.8699 0.0205
-5.000 -0.1288 0.02141 0.01297 -0.0998 0.8603 0.0213
-4.750 -0.1005 0.02051 0.01172 -0.0999 0.8519 0.0224
-4.500 -0.0721 0.01962 0.01049 -0.1001 0.8443 0.0246
-4.250 -0.0441 0.01848 0.00910 -0.1002 0.8364 0.0306
-4.000 -0.0161 0.01776 0.00873 -0.1005 0.8297 0.1226
-3.750 0.0129 0.01842 0.00903 -0.1004 0.8218 0.1521
-3.500 0.0414 0.01850 0.00877 -0.1004 0.8156 0.1622
-3.250 0.0689 0.01881 0.00894 -0.1005 0.8082 0.1771
-3.000 0.0959 0.01909 0.00913 -0.1005 0.8022 0.1941
-2.750 0.1235 0.01888 0.00875 -0.1005 0.7956 0.1985
-2.500 0.1513 0.01859 0.00827 -0.1006 0.7896 0.2002
-2.250 0.1792 0.01835 0.00782 -0.1006 0.7841 0.2019
-2.000 0.2069 0.01815 0.00747 -0.1007 0.7778 0.2035
-1.750 0.2344 0.01789 0.00714 -0.1006 0.7728 0.2052
-1.500 0.2617 0.01771 0.00694 -0.1007 0.7667 0.2077
-1.250 0.2890 0.01756 0.00674 -0.1007 0.7613 0.2107
-1.000 0.3165 0.01743 0.00656 -0.1007 0.7563 0.2136
-0.750 0.3437 0.01734 0.00644 -0.1007 0.7503 0.2160
-0.500 0.3711 0.01724 0.00629 -0.1006 0.7456 0.2183
-0.250 0.3980 0.01714 0.00624 -0.1006 0.7402 0.2208
0.000 0.4250 0.01708 0.00622 -0.1005 0.7347 0.2238
0.250 0.4523 0.01702 0.00615 -0.1004 0.7303 0.2275
0.500 0.4792 0.01705 0.00621 -0.1004 0.7246 0.2316
0.750 0.5063 0.01702 0.00626 -0.1004 0.7194 0.2361
1.000 0.5341 0.01701 0.00626 -0.1003 0.7155 0.2429
1.250 0.5610 0.01707 0.00645 -0.1005 0.7095 0.2517
1.500 0.5885 0.01707 0.00656 -0.1005 0.7046 0.2645
1.750 0.6164 0.01702 0.00666 -0.1006 0.7008 0.2878
2.000 0.6363 0.01587 0.00705 -0.0994 0.6950 0.7228
2.250 0.6679 0.01567 0.00714 -0.0999 0.6902 1.0000
2.500 0.6956 0.01585 0.00733 -0.0998 0.6863 1.0000
2.750 0.7218 0.01616 0.00771 -0.0997 0.6802 1.0000
3.000 0.7490 0.01638 0.00799 -0.0997 0.6756 1.0000
3.250 0.7764 0.01660 0.00831 -0.0996 0.6715 1.0000
3.500 0.8023 0.01694 0.00880 -0.0995 0.6653 1.0000
3.750 0.8295 0.01713 0.00910 -0.0993 0.6602 1.0000
4.000 0.8554 0.01738 0.00954 -0.0990 0.6529 1.0000
4.250 0.8788 0.01655 0.00868 -0.0965 0.6186 1.0000
4.500 0.9009 0.01619 0.00835 -0.0946 0.5790 1.0000
4.750 0.9166 0.01614 0.00784 -0.0913 0.4620 1.0000
5.000 0.9077 0.01943 0.00919 -0.0862 0.1656 1.0000
5.250 0.9109 0.02194 0.01086 -0.0830 0.0330 1.0000
5.500 0.9272 0.02307 0.01211 -0.0812 0.0261 1.0000
5.750 0.9436 0.02414 0.01343 -0.0794 0.0240 1.0000
6.000 0.9587 0.02527 0.01477 -0.0775 0.0225 1.0000
6.250 0.9715 0.02652 0.01619 -0.0753 0.0203 1.0000
6.500 0.9809 0.02798 0.01776 -0.0728 0.0184 1.0000
6.750 0.9870 0.02967 0.01954 -0.0699 0.0175 1.0000
7.000 0.9930 0.03154 0.02145 -0.0669 0.0170 1.0000
7.250 1.0107 0.03367 0.02353 -0.0652 0.0166 1.0000
7.500 1.0393 0.03560 0.02552 -0.0649 0.0163 1.0000
7.750 1.0667 0.03741 0.02751 -0.0643 0.0157 1.0000
8.000 1.0923 0.03928 0.02962 -0.0636 0.0146 1.0000
8.250 1.1187 0.04167 0.03236 -0.0630 0.0140 1.0000
8.500 1.1423 0.04452 0.03552 -0.0620 0.0139 1.0000
8.750 1.1608 0.04752 0.03887 -0.0606 0.0140 1.0000
9.000 1.1744 0.05067 0.04240 -0.0587 0.0142 1.0000
9.250 1.1834 0.05393 0.04602 -0.0565 0.0143 1.0000
9.500 1.1880 0.05728 0.04972 -0.0541 0.0146 1.0000
9.750 1.1882 0.06068 0.05344 -0.0514 0.0148 1.0000
10.000 1.1829 0.06393 0.05698 -0.0483 0.0150 1.0000
10.250 1.1743 0.06726 0.06057 -0.0454 0.0152 1.0000
10.500 1.1634 0.07078 0.06433 -0.0429 0.0154 1.0000
10.750 1.1507 0.07454 0.06832 -0.0410 0.0156 1.0000
11.000 1.1366 0.07862 0.07261 -0.0397 0.0158 1.0000
11.250 1.1218 0.08306 0.07723 -0.0389 0.0160 1.0000
11.500 1.1274 0.08637 0.08069 -0.0382 0.0174 1.0000
11.750 1.1055 0.09056 0.08519 -0.0383 0.0178 1.0000
12.000 1.0812 0.09605 0.09095 -0.0398 0.0182 1.0000
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Polar data table (+)
Polar graphs
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