GOE 115 (MVA MK.2) AIRFOIL (goe115-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 115 (MVA MK.2) AIRFOIL (goe115-il) Reynolds number: 100,000 Max Cl/Cd: 57.64 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe115-il-100000-n5.txt Download as CSV file: xf-goe115-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 115 (MVA MK.2) 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3776 0.09087 0.08607 -0.0408 1.0000 0.0320
-8.750 -0.3804 0.08679 0.08207 -0.0421 1.0000 0.0308
-8.250 -0.4139 0.07306 0.06858 -0.0493 1.0000 0.0265
-8.000 -0.4234 0.06913 0.06475 -0.0502 1.0000 0.0263
-7.750 -0.4320 0.06467 0.06036 -0.0524 1.0000 0.0260
-7.500 -0.4420 0.05965 0.05535 -0.0554 1.0000 0.0257
-7.250 -0.4409 0.05314 0.04863 -0.0617 0.9950 0.0254
-7.000 -0.4186 0.04536 0.04024 -0.0715 0.9824 0.0254
-6.750 -0.3930 0.03966 0.03381 -0.0772 0.9713 0.0258
-6.500 -0.3653 0.03513 0.02853 -0.0811 0.9620 0.0275
-6.250 -0.3364 0.03222 0.02546 -0.0836 0.9537 0.0299
-6.000 -0.3061 0.02932 0.02202 -0.0854 0.9447 0.0314
-5.750 -0.2724 0.02685 0.01900 -0.0872 0.9375 0.0334
-5.500 -0.2425 0.02485 0.01654 -0.0881 0.9275 0.0366
-5.250 -0.2113 0.02291 0.01444 -0.0891 0.9190 0.0388
-5.000 -0.1793 0.02158 0.01295 -0.0901 0.9102 0.0425
-4.750 -0.1494 0.02057 0.01175 -0.0904 0.8997 0.0454
-4.500 -0.1201 0.01937 0.01048 -0.0909 0.8899 0.0474
-4.250 -0.0896 0.01854 0.00954 -0.0916 0.8803 0.0522
-4.000 -0.0610 0.01793 0.00870 -0.0917 0.8687 0.0550
-3.750 -0.0319 0.01740 0.00794 -0.0919 0.8575 0.0571
-3.500 -0.0028 0.01680 0.00719 -0.0921 0.8469 0.0610
-3.250 0.0269 0.01633 0.00652 -0.0924 0.8371 0.0677
-3.000 0.0540 0.01571 0.00595 -0.0923 0.8258 0.0907
-2.750 0.0801 0.01511 0.00595 -0.0923 0.8149 0.2422
-2.500 0.1086 0.01518 0.00588 -0.0923 0.8047 0.2822
-2.250 0.1370 0.01515 0.00567 -0.0922 0.7949 0.2972
-2.000 0.1641 0.01515 0.00556 -0.0919 0.7843 0.3137
-1.750 0.1918 0.01512 0.00539 -0.0918 0.7753 0.3235
-1.500 0.2195 0.01508 0.00523 -0.0917 0.7667 0.3336
-1.250 0.2463 0.01506 0.00517 -0.0915 0.7574 0.3478
-0.750 0.3006 0.01499 0.00503 -0.0912 0.7409 0.3773
-0.500 0.3278 0.01495 0.00499 -0.0910 0.7339 0.3955
-0.250 0.3542 0.01489 0.00502 -0.0908 0.7264 0.4193
0.250 0.4089 0.01482 0.00501 -0.0906 0.7130 0.4519
0.500 0.4367 0.01476 0.00499 -0.0905 0.7074 0.4697
0.750 0.4629 0.01472 0.00510 -0.0903 0.7005 0.4986
1.000 0.4891 0.01455 0.00518 -0.0900 0.6951 0.5616
1.500 0.5603 0.01390 0.00539 -0.0929 0.6841 1.0000
1.750 0.5875 0.01407 0.00548 -0.0927 0.6792 1.0000
2.000 0.6134 0.01429 0.00569 -0.0925 0.6729 1.0000
2.250 0.6399 0.01448 0.00586 -0.0922 0.6665 1.0000
2.500 0.6658 0.01467 0.00604 -0.0917 0.6592 1.0000
2.750 0.6919 0.01484 0.00620 -0.0913 0.6514 1.0000
3.000 0.7173 0.01504 0.00645 -0.0908 0.6433 1.0000
3.250 0.7437 0.01523 0.00666 -0.0904 0.6365 1.0000
3.500 0.7693 0.01548 0.00700 -0.0901 0.6303 1.0000
3.750 0.7951 0.01573 0.00736 -0.0897 0.6241 1.0000
4.000 0.8216 0.01597 0.00768 -0.0894 0.6187 1.0000
4.250 0.8464 0.01626 0.00813 -0.0889 0.6116 1.0000
4.500 0.8733 0.01649 0.00845 -0.0885 0.6057 1.0000
4.750 0.8972 0.01660 0.00871 -0.0875 0.5916 1.0000
5.000 0.9182 0.01657 0.00877 -0.0857 0.5664 1.0000
5.250 0.9364 0.01643 0.00861 -0.0832 0.5239 1.0000
5.500 0.9528 0.01653 0.00864 -0.0806 0.4622 1.0000
5.750 0.9533 0.01797 0.00898 -0.0759 0.2900 1.0000
6.000 0.9390 0.02149 0.01093 -0.0706 0.0655 1.0000
6.250 0.9504 0.02289 0.01235 -0.0680 0.0470 1.0000
6.500 0.9620 0.02417 0.01372 -0.0656 0.0390 1.0000
6.750 0.9748 0.02527 0.01495 -0.0634 0.0337 1.0000
7.000 0.9814 0.02676 0.01655 -0.0605 0.0312 1.0000
7.250 0.9895 0.02799 0.01793 -0.0577 0.0294 1.0000
7.500 0.9973 0.02922 0.01929 -0.0549 0.0271 1.0000
7.750 1.0053 0.03053 0.02067 -0.0523 0.0249 1.0000
8.000 1.0139 0.03207 0.02224 -0.0500 0.0235 1.0000
8.250 1.0268 0.03388 0.02407 -0.0481 0.0224 1.0000
8.500 1.0562 0.03640 0.02657 -0.0481 0.0213 1.0000
8.750 1.0823 0.03816 0.02855 -0.0476 0.0202 1.0000
9.000 1.1081 0.04024 0.03090 -0.0472 0.0185 1.0000
9.250 1.1359 0.04310 0.03406 -0.0471 0.0180 1.0000
9.500 1.1556 0.04608 0.03737 -0.0461 0.0176 1.0000
9.750 1.1689 0.04911 0.04076 -0.0444 0.0174 1.0000
10.000 1.1757 0.05222 0.04423 -0.0421 0.0173 1.0000
10.250 1.1768 0.05524 0.04758 -0.0394 0.0172 1.0000
10.500 1.1736 0.05820 0.05084 -0.0366 0.0171 1.0000
10.750 1.1667 0.06116 0.05409 -0.0339 0.0168 1.0000
11.000 1.1576 0.06437 0.05763 -0.0316 0.0168 1.0000
11.250 1.1462 0.06770 0.06122 -0.0298 0.0165 1.0000
11.500 1.1327 0.07143 0.06519 -0.0286 0.0165 1.0000
11.750 1.1178 0.07545 0.06944 -0.0281 0.0163 1.0000
12.000 1.1017 0.07991 0.07413 -0.0283 0.0164 1.0000
12.250 1.0840 0.08481 0.07922 -0.0292 0.0163 1.0000
12.500 1.0650 0.09032 0.08493 -0.0310 0.0163 1.0000
12.750 1.0450 0.09655 0.09135 -0.0335 0.0167 1.0000
13.000 1.0250 0.10318 0.09809 -0.0368 0.0167 1.0000
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Polar data table (+)
Polar graphs
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