GOE 311 (MVA H.43) AIRFOIL (goe311-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 311 (MVA H.43) AIRFOIL (goe311-il) Reynolds number: 500,000 Max Cl/Cd: 113.98 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe311-il-500000.txt Download as CSV file: xf-goe311-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 311 (MVA H.43) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2618 0.08699 0.08496 -0.0341 0.9491 0.0245
-7.500 -0.2592 0.08424 0.08220 -0.0349 0.9334 0.0254
-7.250 -0.2522 0.08009 0.07801 -0.0419 0.9165 0.0273
-7.000 -0.2384 0.07582 0.07369 -0.0476 0.9011 0.0276
-6.750 -0.2693 0.02039 0.01646 -0.0848 0.8892 0.0161
-6.500 -0.2461 0.01774 0.01331 -0.0848 0.8765 0.0166
-6.250 -0.2218 0.01602 0.01119 -0.0843 0.8623 0.0170
-6.000 -0.1972 0.01444 0.00929 -0.0839 0.8467 0.0183
-5.750 -0.1711 0.01378 0.00846 -0.0835 0.8298 0.0198
-5.500 -0.1445 0.01311 0.00754 -0.0831 0.8123 0.0214
-5.250 -0.1178 0.01241 0.00663 -0.0827 0.7948 0.0236
-5.000 -0.0901 0.01218 0.00627 -0.0824 0.7778 0.0268
-4.750 -0.0620 0.01229 0.00634 -0.0822 0.7618 0.0313
-4.500 -0.0335 0.01260 0.00659 -0.0821 0.7467 0.0373
-4.250 -0.0049 0.01321 0.00715 -0.0820 0.7317 0.0427
-4.000 0.0225 0.01286 0.00661 -0.0820 0.7170 0.0469
-3.750 0.0502 0.01273 0.00641 -0.0820 0.7014 0.0503
-3.500 0.0782 0.01263 0.00618 -0.0819 0.6842 0.0534
-3.250 0.1064 0.01275 0.00615 -0.0819 0.6653 0.0554
-3.000 0.1337 0.01178 0.00495 -0.0819 0.6468 0.0588
-2.750 0.1615 0.01148 0.00455 -0.0818 0.6282 0.0616
-2.500 0.1894 0.01129 0.00423 -0.0818 0.6116 0.0642
-2.250 0.2174 0.01105 0.00384 -0.0818 0.5984 0.0650
-2.000 0.2454 0.01084 0.00350 -0.0817 0.5879 0.0655
-1.750 0.2735 0.01065 0.00322 -0.0817 0.5799 0.0660
-1.500 0.3015 0.01052 0.00298 -0.0816 0.5733 0.0665
-1.250 0.3297 0.01039 0.00279 -0.0816 0.5675 0.0671
-1.000 0.3578 0.01030 0.00264 -0.0816 0.5621 0.0679
-0.750 0.3858 0.01022 0.00250 -0.0815 0.5577 0.0704
-0.500 0.4141 0.01013 0.00241 -0.0816 0.5535 0.0737
-0.250 0.4423 0.01007 0.00236 -0.0816 0.5493 0.0784
0.000 0.4703 0.01005 0.00240 -0.0816 0.5454 0.0973
0.250 0.4985 0.01014 0.00248 -0.0816 0.5416 0.1165
0.500 0.5270 0.01019 0.00255 -0.0817 0.5381 0.1272
0.750 0.5554 0.01028 0.00260 -0.0818 0.5341 0.1341
1.000 0.5834 0.01038 0.00268 -0.0818 0.5295 0.1412
1.250 0.6116 0.01049 0.00276 -0.0819 0.5247 0.1463
1.500 0.6396 0.01049 0.00279 -0.0819 0.5196 0.1513
1.750 0.6675 0.01058 0.00287 -0.0820 0.5148 0.1570
2.000 0.6955 0.01068 0.00294 -0.0820 0.5104 0.1614
2.250 0.7235 0.01063 0.00296 -0.0821 0.5054 0.1660
2.500 0.7512 0.01067 0.00299 -0.0821 0.4996 0.1707
2.750 0.7790 0.01072 0.00306 -0.0821 0.4938 0.1760
3.000 0.8069 0.01068 0.00309 -0.0822 0.4883 0.1828
3.250 0.8346 0.01074 0.00315 -0.0822 0.4841 0.1900
3.500 0.8624 0.01078 0.00327 -0.0823 0.4803 0.2020
3.750 0.8904 0.01075 0.00337 -0.0824 0.4759 0.2234
4.000 0.9180 0.01068 0.00350 -0.0825 0.4715 0.2925
4.250 0.9457 0.00943 0.00363 -0.0826 0.4672 1.0000
4.500 0.9732 0.00948 0.00373 -0.0826 0.4624 1.0000
4.750 1.0005 0.00955 0.00382 -0.0826 0.4570 1.0000
5.000 1.0274 0.00969 0.00392 -0.0825 0.4518 1.0000
5.250 1.0550 0.00974 0.00404 -0.0825 0.4456 1.0000
5.500 1.0819 0.00984 0.00414 -0.0824 0.4384 1.0000
5.750 1.1089 0.00991 0.00423 -0.0823 0.4267 1.0000
6.000 1.1356 0.01001 0.00433 -0.0822 0.4123 1.0000
6.250 1.1615 0.01019 0.00447 -0.0820 0.3938 1.0000
6.500 1.1862 0.01050 0.00466 -0.0817 0.3620 1.0000
6.750 1.2087 0.01107 0.00502 -0.0811 0.3220 1.0000
7.000 1.2297 0.01181 0.00552 -0.0803 0.2783 1.0000
7.250 1.2501 0.01259 0.00609 -0.0795 0.2372 1.0000
7.500 1.2695 0.01346 0.00673 -0.0786 0.1963 1.0000
7.750 1.2864 0.01452 0.00750 -0.0773 0.1506 1.0000
8.000 1.2964 0.01614 0.00867 -0.0751 0.0823 1.0000
8.250 1.3139 0.01699 0.00946 -0.0738 0.0598 1.0000
8.500 1.3230 0.01848 0.01070 -0.0713 0.0225 1.0000
8.750 1.3397 0.01925 0.01155 -0.0698 0.0193 1.0000
9.000 1.3557 0.02001 0.01241 -0.0682 0.0177 1.0000
9.250 1.3681 0.02090 0.01339 -0.0661 0.0166 1.0000
9.500 1.3747 0.02201 0.01459 -0.0632 0.0156 1.0000
9.750 1.3769 0.02349 0.01620 -0.0601 0.0148 1.0000
10.000 1.3800 0.02505 0.01789 -0.0574 0.0144 1.0000
10.250 1.3869 0.02645 0.01938 -0.0555 0.0141 1.0000
10.500 1.3921 0.02807 0.02110 -0.0537 0.0137 1.0000
10.750 1.3962 0.02991 0.02303 -0.0521 0.0132 1.0000
11.000 1.3993 0.03196 0.02518 -0.0508 0.0127 1.0000
11.250 1.4014 0.03425 0.02757 -0.0497 0.0122 1.0000
11.500 1.4018 0.03683 0.03024 -0.0488 0.0119 1.0000
11.750 1.4006 0.03965 0.03315 -0.0480 0.0116 1.0000
12.000 1.3982 0.04267 0.03626 -0.0473 0.0114 1.0000
12.250 1.3943 0.04586 0.03953 -0.0466 0.0112 1.0000
12.500 1.3892 0.04919 0.04295 -0.0458 0.0110 1.0000
12.750 1.3837 0.05246 0.04628 -0.0448 0.0108 1.0000
13.000 1.3798 0.05536 0.04924 -0.0431 0.0106 1.0000
13.250 1.3816 0.05771 0.05165 -0.0415 0.0104 1.0000
13.500 1.3855 0.06023 0.05428 -0.0413 0.0103 1.0000
13.750 1.3893 0.06271 0.05687 -0.0408 0.0102 1.0000
14.000 1.3932 0.06519 0.05945 -0.0401 0.0100 1.0000
14.250 1.3966 0.06773 0.06209 -0.0395 0.0099 1.0000
14.500 1.3993 0.07044 0.06492 -0.0391 0.0097 1.0000
14.750 1.4010 0.07335 0.06795 -0.0390 0.0095 1.0000
15.000 1.4021 0.07639 0.07113 -0.0389 0.0093 1.0000
15.250 1.4021 0.07963 0.07449 -0.0390 0.0090 1.0000
15.500 1.4016 0.08293 0.07791 -0.0391 0.0089 1.0000
15.750 1.4000 0.08645 0.08157 -0.0392 0.0088 1.0000
16.000 1.3969 0.09027 0.08554 -0.0395 0.0087 1.0000
16.250 1.3922 0.09440 0.08983 -0.0401 0.0087 1.0000
16.500 1.3855 0.09894 0.09454 -0.0410 0.0087 1.0000
16.750 1.3767 0.10396 0.09974 -0.0422 0.0088 1.0000
17.000 1.3667 0.10933 0.10529 -0.0439 0.0088 1.0000
17.250 1.3551 0.11512 0.11126 -0.0459 0.0089 1.0000
17.500 1.3420 0.12133 0.11766 -0.0484 0.0090 1.0000
17.750 1.3285 0.12790 0.12441 -0.0515 0.0091 1.0000
18.000 1.3135 0.13501 0.13170 -0.0551 0.0093 1.0000
18.250 1.2985 0.14245 0.13931 -0.0592 0.0094 1.0000
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Polar data table (+)
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