GOE 114 (MVA MK.1) AIRFOIL (goe114-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 114 (MVA MK.1) AIRFOIL (goe114-il) Reynolds number: 50,000 Max Cl/Cd: 35.42 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe114-il-50000.txt Download as CSV file: xf-goe114-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3590 0.10179 0.09539 -0.0295 1.0000 0.2579
-8.000 -0.3726 0.10106 0.09481 -0.0291 1.0000 0.2651
-7.750 -0.3742 0.09803 0.09189 -0.0285 1.0000 0.2670
-7.500 -0.3713 0.09467 0.08860 -0.0276 1.0000 0.2684
-7.250 -0.3738 0.09202 0.08605 -0.0264 1.0000 0.2697
-7.000 -0.3816 0.08989 0.08405 -0.0247 1.0000 0.2704
-6.750 -0.3947 0.08812 0.08242 -0.0223 1.0000 0.2705
-6.500 -0.4110 0.08652 0.08097 -0.0199 1.0000 0.2697
-5.500 -0.4621 0.05637 0.05059 -0.0491 1.0000 0.1155
-5.250 -0.4502 0.04841 0.04194 -0.0547 1.0000 0.1041
-5.000 -0.4309 0.04193 0.03425 -0.0582 1.0000 0.0948
-4.750 -0.4110 0.03845 0.03051 -0.0578 1.0000 0.0910
-4.500 -0.3878 0.03504 0.02647 -0.0577 1.0000 0.0863
-4.250 -0.3622 0.03259 0.02319 -0.0570 1.0000 0.0823
-4.000 -0.3383 0.03070 0.02091 -0.0559 1.0000 0.0811
-3.750 -0.3156 0.02903 0.01902 -0.0546 1.0000 0.0808
-3.500 -0.2936 0.02768 0.01750 -0.0532 1.0000 0.0818
-3.250 -0.2712 0.02646 0.01606 -0.0523 1.0000 0.0843
-3.000 -0.2488 0.02554 0.01499 -0.0515 1.0000 0.0918
-2.750 -0.2230 0.02446 0.01395 -0.0516 1.0000 0.1159
-2.500 -0.1984 0.02378 0.01425 -0.0514 1.0000 0.3086
-2.250 -0.1855 0.02478 0.01517 -0.0486 1.0000 0.3906
-2.000 -0.1709 0.02526 0.01559 -0.0462 1.0000 0.4378
-1.750 -0.1554 0.02551 0.01578 -0.0440 1.0000 0.4783
-1.500 -0.1458 0.02573 0.01625 -0.0404 1.0000 0.5410
-1.250 -0.1329 0.02573 0.01631 -0.0376 1.0000 0.5916
-1.000 -0.1154 0.02565 0.01603 -0.0361 1.0000 0.6251
-0.750 -0.0935 0.02566 0.01583 -0.0362 1.0000 0.6437
-0.500 -0.0716 0.02569 0.01573 -0.0362 1.0000 0.6618
-0.250 -0.0490 0.02581 0.01575 -0.0366 1.0000 0.6795
0.000 -0.0262 0.02598 0.01586 -0.0371 1.0000 0.6994
0.250 -0.0038 0.02615 0.01609 -0.0375 1.0000 0.7252
0.500 0.0185 0.02624 0.01634 -0.0377 1.0000 0.7697
0.750 0.0704 0.02665 0.01694 -0.0450 0.9862 1.0000
1.000 0.1198 0.02794 0.01785 -0.0514 0.9741 1.0000
1.250 0.1631 0.02912 0.01874 -0.0563 0.9623 1.0000
1.500 0.2032 0.03024 0.01964 -0.0603 0.9504 1.0000
1.750 0.2411 0.03135 0.02058 -0.0637 0.9389 1.0000
2.000 0.2787 0.03244 0.02157 -0.0669 0.9274 1.0000
2.250 0.3130 0.03349 0.02257 -0.0694 0.9161 1.0000
2.500 0.3415 0.03445 0.02352 -0.0708 0.9043 1.0000
2.750 0.3688 0.03546 0.02461 -0.0721 0.8929 1.0000
3.000 0.3961 0.03651 0.02571 -0.0733 0.8818 1.0000
3.250 0.4246 0.03760 0.02689 -0.0746 0.8710 1.0000
3.500 0.4568 0.03874 0.02816 -0.0765 0.8609 1.0000
3.750 0.4816 0.03985 0.02943 -0.0772 0.8504 1.0000
4.000 0.5003 0.04103 0.03076 -0.0771 0.8400 1.0000
4.250 0.7409 0.02092 0.01128 -0.0739 0.5160 1.0000
4.500 0.7307 0.02352 0.01182 -0.0673 0.1652 1.0000
4.750 0.7355 0.02597 0.01362 -0.0642 0.0955 1.0000
5.000 0.7492 0.02739 0.01513 -0.0618 0.0863 1.0000
5.250 0.7614 0.02883 0.01672 -0.0593 0.0820 1.0000
5.500 0.7703 0.03044 0.01847 -0.0564 0.0798 1.0000
5.750 0.7793 0.03197 0.02011 -0.0534 0.0790 1.0000
6.000 0.7935 0.03351 0.02179 -0.0508 0.0786 1.0000
6.250 0.8316 0.03511 0.02354 -0.0506 0.0766 1.0000
6.500 0.9084 0.03781 0.02629 -0.0546 0.0756 1.0000
6.750 0.9683 0.04130 0.02991 -0.0570 0.0811 1.0000
7.000 1.0059 0.04457 0.03385 -0.0565 0.0889 1.0000
7.250 1.0357 0.04739 0.03732 -0.0547 0.0981 1.0000
7.500 1.0630 0.05064 0.04116 -0.0529 0.1095 1.0000
7.750 1.0836 0.05406 0.04531 -0.0503 0.1244 1.0000
8.000 1.1101 0.05875 0.05052 -0.0489 0.1446 1.0000
8.250 1.1077 0.06177 0.05451 -0.0450 0.1617 1.0000
8.500 1.1138 0.06696 0.06030 -0.0433 0.1842 1.0000
8.750 1.0958 0.07173 0.06561 -0.0409 0.1979 1.0000
9.000 1.0650 0.07605 0.07024 -0.0385 0.2010 1.0000
9.250 1.0379 0.08074 0.07506 -0.0369 0.2046 1.0000
9.500 1.0046 0.08508 0.07945 -0.0357 0.2026 1.0000
9.750 0.9725 0.09065 0.08503 -0.0369 0.2013 1.0000
10.000 0.9421 0.09738 0.09172 -0.0401 0.2005 1.0000
10.250 0.9174 0.10663 0.10092 -0.0460 0.2107 1.0000
10.500 0.8842 0.11538 0.10953 -0.0526 0.2138 1.0000
10.750 0.8509 0.12691 0.12080 -0.0623 0.2527 1.0000
11.000 0.7441 0.12150 0.11588 -0.0460 0.1873 1.0000
11.250 0.7123 0.13207 0.12639 -0.0540 0.2318 1.0000
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Polar data table (+)
Polar graphs
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