GOE 115 (MVA MK.2) AIRFOIL (goe115-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 115 (MVA MK.2) AIRFOIL (goe115-il) Reynolds number: 200,000 Max Cl/Cd: 77.62 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe115-il-200000.txt Download as CSV file: xf-goe115-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2907 0.08941 0.08615 -0.0398 1.0000 0.0505
-9.250 -0.3006 0.08505 0.08185 -0.0426 1.0000 0.0538
-9.000 -0.3135 0.08064 0.07752 -0.0458 1.0000 0.0546
-8.750 -0.3247 0.07640 0.07334 -0.0481 1.0000 0.0549
-8.500 -0.3013 0.07458 0.07152 -0.0421 1.0000 0.0594
-8.250 -0.3035 0.07162 0.06861 -0.0419 1.0000 0.0620
-8.000 -0.3146 0.06828 0.06535 -0.0421 1.0000 0.0646
-7.000 -0.4300 0.06826 0.06543 -0.0415 0.9974 0.0610
-6.750 -0.3994 0.05235 0.04920 -0.0679 0.9856 0.0700
-6.500 -0.3714 0.04599 0.04243 -0.0777 0.9763 0.0829
-6.250 -0.3388 0.04344 0.03987 -0.0813 0.9713 0.0968
-6.000 -0.3067 0.04380 0.04038 -0.0810 0.9655 0.1119
-5.750 -0.2728 0.04227 0.03876 -0.0843 0.9590 0.1372
-5.250 -0.1985 0.02107 0.01442 -0.0941 0.9435 0.0501
-5.000 -0.1643 0.01914 0.01215 -0.0950 0.9352 0.0494
-4.750 -0.1271 0.01778 0.01059 -0.0966 0.9284 0.0518
-4.500 -0.0956 0.01652 0.00919 -0.0970 0.9179 0.0523
-4.250 -0.0639 0.01551 0.00809 -0.0974 0.9077 0.0535
-4.000 -0.0335 0.01462 0.00712 -0.0977 0.8972 0.0560
-3.750 -0.0064 0.01380 0.00626 -0.0974 0.8847 0.0579
-3.500 0.0202 0.01329 0.00564 -0.0969 0.8712 0.0603
-3.250 0.0469 0.01294 0.00514 -0.0964 0.8577 0.0633
-3.000 0.0735 0.01266 0.00471 -0.0959 0.8445 0.0688
-2.750 0.0999 0.01230 0.00426 -0.0954 0.8320 0.0798
-2.500 0.1242 0.01152 0.00409 -0.0949 0.8200 0.2376
-2.250 0.1516 0.01164 0.00414 -0.0945 0.8090 0.2843
-2.000 0.1787 0.01173 0.00412 -0.0942 0.7983 0.3069
-1.750 0.2051 0.01180 0.00412 -0.0938 0.7869 0.3243
-1.500 0.2317 0.01190 0.00412 -0.0934 0.7769 0.3451
-1.250 0.2588 0.01188 0.00404 -0.0931 0.7687 0.3559
-1.000 0.2852 0.01187 0.00402 -0.0929 0.7592 0.3667
-0.750 0.3123 0.01188 0.00398 -0.0927 0.7518 0.3780
-0.500 0.3390 0.01188 0.00396 -0.0924 0.7437 0.3905
-0.250 0.3656 0.01185 0.00398 -0.0922 0.7368 0.4079
0.000 0.3920 0.01182 0.00401 -0.0919 0.7295 0.4268
0.250 0.4189 0.01181 0.00403 -0.0918 0.7237 0.4465
0.500 0.4453 0.01177 0.00408 -0.0916 0.7172 0.4622
0.750 0.4723 0.01170 0.00410 -0.0914 0.7121 0.4808
1.000 0.4978 0.01160 0.00420 -0.0910 0.7051 0.5113
1.250 0.5215 0.01122 0.00425 -0.0901 0.6989 0.6229
1.500 0.5745 0.01056 0.00427 -0.0951 0.6918 1.0000
1.750 0.6014 0.01070 0.00433 -0.0949 0.6855 1.0000
2.000 0.6279 0.01087 0.00446 -0.0946 0.6793 1.0000
2.250 0.6543 0.01102 0.00458 -0.0942 0.6725 1.0000
2.500 0.6812 0.01119 0.00471 -0.0940 0.6669 1.0000
2.750 0.7071 0.01138 0.00494 -0.0937 0.6609 1.0000
3.000 0.7342 0.01156 0.00513 -0.0935 0.6559 1.0000
3.250 0.7604 0.01178 0.00540 -0.0932 0.6505 1.0000
3.500 0.7867 0.01199 0.00566 -0.0929 0.6449 1.0000
3.750 0.8136 0.01217 0.00584 -0.0926 0.6386 1.0000
4.000 0.8388 0.01220 0.00587 -0.0917 0.6257 1.0000
4.250 0.8621 0.01216 0.00586 -0.0904 0.6082 1.0000
4.500 0.8849 0.01208 0.00578 -0.0890 0.5871 1.0000
4.750 0.9075 0.01203 0.00573 -0.0876 0.5649 1.0000
5.000 0.9283 0.01196 0.00570 -0.0858 0.5317 1.0000
5.250 0.9376 0.01232 0.00552 -0.0817 0.3898 1.0000
5.500 0.9170 0.01617 0.00735 -0.0747 0.0755 1.0000
5.750 0.9299 0.01748 0.00863 -0.0722 0.0520 1.0000
6.000 0.9413 0.01877 0.01001 -0.0695 0.0444 1.0000
6.250 0.9557 0.01976 0.01110 -0.0673 0.0415 1.0000
6.500 0.9684 0.02087 0.01227 -0.0648 0.0390 1.0000
6.750 0.9806 0.02203 0.01349 -0.0624 0.0369 1.0000
7.000 0.9899 0.02365 0.01507 -0.0597 0.0338 1.0000
7.250 1.0068 0.02563 0.01703 -0.0580 0.0324 1.0000
7.500 1.0301 0.02702 0.01849 -0.0571 0.0315 1.0000
7.750 1.0586 0.02888 0.02044 -0.0570 0.0309 1.0000
8.000 1.0901 0.03119 0.02287 -0.0572 0.0308 1.0000
8.250 1.1146 0.03292 0.02481 -0.0564 0.0294 1.0000
8.500 1.1411 0.03551 0.02764 -0.0559 0.0293 1.0000
8.750 1.1679 0.03972 0.03212 -0.0555 0.0311 1.0000
16.500 0.7571 0.19177 0.18884 -0.0833 0.0410 1.0000
16.750 0.7577 0.19564 0.19272 -0.0856 0.0383 1.0000
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Polar data table (+)
Polar graphs
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