GOE 425 AIRFOIL (goe425-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 425 AIRFOIL (goe425-il) Reynolds number: 500,000 Max Cl/Cd: 111 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe425-il-500000.txt Download as CSV file: xf-goe425-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 425 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2990 0.10977 0.10674 -0.0406 0.7819 0.0353
-11.000 -0.2955 0.10623 0.10314 -0.0423 0.7696 0.0362
-10.750 -0.3319 0.09212 0.08905 -0.0535 0.7662 0.0387
-10.500 -0.3234 0.09018 0.08705 -0.0532 0.7557 0.0389
-10.250 -0.3145 0.08820 0.08501 -0.0535 0.7461 0.0392
-10.000 -0.3067 0.08585 0.08263 -0.0542 0.7379 0.0396
-9.750 -0.3008 0.08307 0.07981 -0.0555 0.7301 0.0400
-9.500 -0.2978 0.07949 0.07620 -0.0577 0.7235 0.0407
-9.250 -0.2997 0.07454 0.07125 -0.0613 0.7171 0.0416
-9.000 -0.3688 0.03643 0.03267 -0.0886 0.7053 0.0452
-8.750 -0.3557 0.03427 0.03048 -0.0886 0.6985 0.0455
-8.500 -0.3446 0.03209 0.02820 -0.0885 0.6922 0.0459
-8.250 -0.3321 0.02996 0.02601 -0.0885 0.6856 0.0464
-8.000 -0.3204 0.02763 0.02354 -0.0885 0.6791 0.0473
-7.750 -0.3302 0.02207 0.01713 -0.0876 0.6744 0.0519
-7.500 -0.3086 0.02028 0.01543 -0.0877 0.6681 0.0526
-7.250 -0.2877 0.01898 0.01410 -0.0876 0.6616 0.0533
-7.000 -0.2672 0.01780 0.01280 -0.0873 0.6557 0.0546
-6.750 -0.2532 0.01553 0.01011 -0.0865 0.6496 0.0602
-6.500 -0.2488 0.02212 0.01556 -0.0863 0.6532 0.0425
-6.250 -0.2252 0.02003 0.01312 -0.0856 0.6468 0.0403
-6.000 -0.1999 0.01900 0.01187 -0.0852 0.6407 0.0401
-5.750 -0.1736 0.01821 0.01100 -0.0850 0.6344 0.0405
-5.500 -0.1472 0.01739 0.01005 -0.0847 0.6278 0.0405
-5.250 -0.1207 0.01669 0.00922 -0.0844 0.6221 0.0405
-5.000 -0.0938 0.01604 0.00851 -0.0842 0.6165 0.0406
-4.750 -0.0669 0.01547 0.00788 -0.0839 0.6108 0.0409
-4.500 -0.0403 0.01498 0.00731 -0.0837 0.6057 0.0411
-4.250 -0.0134 0.01451 0.00681 -0.0835 0.6006 0.0415
-4.000 0.0135 0.01408 0.00635 -0.0832 0.5952 0.0419
-3.750 0.0402 0.01373 0.00594 -0.0830 0.5904 0.0425
-3.500 0.0672 0.01345 0.00561 -0.0828 0.5861 0.0433
-3.250 0.0945 0.01316 0.00530 -0.0826 0.5818 0.0439
-3.000 0.1217 0.01290 0.00501 -0.0825 0.5774 0.0443
-2.750 0.1478 0.01250 0.00456 -0.0821 0.5733 0.0450
-2.500 0.1742 0.01218 0.00421 -0.0819 0.5694 0.0460
-2.250 0.2015 0.01192 0.00397 -0.0818 0.5658 0.0471
-2.000 0.2291 0.01173 0.00376 -0.0817 0.5620 0.0484
-1.750 0.2567 0.01159 0.00358 -0.0816 0.5584 0.0499
-1.500 0.2844 0.01151 0.00343 -0.0816 0.5547 0.0520
-1.250 0.3122 0.01135 0.00327 -0.0815 0.5516 0.0557
-1.000 0.3401 0.01122 0.00315 -0.0815 0.5482 0.0620
-0.750 0.3674 0.01096 0.00310 -0.0814 0.5448 0.1172
-0.500 0.3917 0.01024 0.00297 -0.0812 0.5416 0.2991
-0.250 0.4166 0.00983 0.00303 -0.0809 0.5384 0.4599
0.000 0.4439 0.00978 0.00311 -0.0808 0.5353 0.5135
0.250 0.4714 0.00972 0.00316 -0.0808 0.5322 0.5506
0.500 0.4992 0.00970 0.00320 -0.0807 0.5290 0.5791
0.750 0.5267 0.00968 0.00325 -0.0806 0.5259 0.6048
1.000 0.5541 0.00968 0.00330 -0.0805 0.5230 0.6364
1.250 0.5811 0.00972 0.00340 -0.0803 0.5197 0.6721
1.500 0.6069 0.00956 0.00347 -0.0799 0.5171 0.7246
1.750 0.6294 0.00924 0.00357 -0.0785 0.5143 0.8344
2.250 0.7421 0.00928 0.00374 -0.0905 0.5076 1.0000
2.500 0.7683 0.00944 0.00382 -0.0903 0.5045 1.0000
2.750 0.7943 0.00958 0.00393 -0.0900 0.5017 1.0000
3.000 0.8202 0.00966 0.00402 -0.0896 0.4990 1.0000
3.250 0.8461 0.00975 0.00410 -0.0893 0.4961 1.0000
3.500 0.8721 0.00986 0.00419 -0.0890 0.4932 1.0000
3.750 0.8981 0.00998 0.00427 -0.0886 0.4902 1.0000
4.000 0.9245 0.01020 0.00441 -0.0884 0.4864 1.0000
4.250 0.9498 0.01025 0.00451 -0.0880 0.4832 1.0000
4.500 0.9755 0.01033 0.00461 -0.0876 0.4796 1.0000
4.750 1.0015 0.01043 0.00471 -0.0873 0.4762 1.0000
5.000 1.0275 0.01056 0.00481 -0.0870 0.4729 1.0000
5.250 1.0537 0.01077 0.00497 -0.0868 0.4693 1.0000
5.500 1.0792 0.01084 0.00511 -0.0865 0.4658 1.0000
5.750 1.1049 0.01094 0.00523 -0.0862 0.4620 1.0000
6.000 1.1306 0.01104 0.00533 -0.0859 0.4580 1.0000
6.250 1.1565 0.01124 0.00547 -0.0856 0.4537 1.0000
6.500 1.1817 0.01132 0.00564 -0.0852 0.4496 1.0000
6.750 1.2070 0.01141 0.00577 -0.0849 0.4450 1.0000
7.000 1.2321 0.01154 0.00588 -0.0845 0.4401 1.0000
7.250 1.2571 0.01170 0.00606 -0.0841 0.4354 1.0000
7.500 1.2822 0.01181 0.00624 -0.0838 0.4305 1.0000
7.750 1.3069 0.01196 0.00639 -0.0834 0.4256 1.0000
8.000 1.3312 0.01216 0.00659 -0.0829 0.4206 1.0000
8.250 1.3557 0.01228 0.00679 -0.0825 0.4146 1.0000
8.500 1.3791 0.01246 0.00697 -0.0819 0.4082 1.0000
8.750 1.4029 0.01266 0.00722 -0.0814 0.4026 1.0000
9.000 1.4263 0.01285 0.00745 -0.0809 0.3961 1.0000
9.250 1.4481 0.01311 0.00770 -0.0801 0.3892 1.0000
9.500 1.4702 0.01333 0.00798 -0.0793 0.3801 1.0000
9.750 1.4904 0.01364 0.00829 -0.0783 0.3707 1.0000
10.000 1.5085 0.01402 0.00865 -0.0770 0.3600 1.0000
10.250 1.5273 0.01438 0.00904 -0.0758 0.3488 1.0000
10.500 1.5422 0.01483 0.00950 -0.0739 0.3374 1.0000
10.750 1.5540 0.01541 0.01005 -0.0717 0.3244 1.0000
11.000 1.5640 0.01612 0.01074 -0.0693 0.3096 1.0000
11.250 1.5720 0.01700 0.01159 -0.0670 0.2932 1.0000
11.500 1.5763 0.01817 0.01271 -0.0644 0.2732 1.0000
11.750 1.5739 0.01991 0.01434 -0.0616 0.2474 1.0000
12.000 1.5615 0.02263 0.01690 -0.0587 0.2136 1.0000
12.250 1.5459 0.02604 0.02017 -0.0564 0.1862 1.0000
12.500 1.5348 0.02933 0.02339 -0.0548 0.1703 1.0000
12.750 1.5285 0.03228 0.02634 -0.0536 0.1598 1.0000
13.000 1.5217 0.03532 0.02939 -0.0524 0.1516 1.0000
13.250 1.5189 0.03802 0.03212 -0.0514 0.1439 1.0000
13.500 1.5128 0.04106 0.03519 -0.0505 0.1370 1.0000
13.750 1.5100 0.04385 0.03801 -0.0497 0.1293 1.0000
14.000 1.5053 0.04691 0.04110 -0.0490 0.1226 1.0000
14.250 1.5021 0.04990 0.04410 -0.0485 0.1153 1.0000
14.500 1.4985 0.05300 0.04723 -0.0480 0.1090 1.0000
14.750 1.4946 0.05620 0.05044 -0.0477 0.1027 1.0000
15.000 1.4907 0.05944 0.05371 -0.0474 0.0975 1.0000
15.250 1.4874 0.06266 0.05696 -0.0472 0.0927 1.0000
15.500 1.4825 0.06611 0.06043 -0.0470 0.0885 1.0000
15.750 1.4818 0.06908 0.06346 -0.0469 0.0851 1.0000
16.000 1.4785 0.07239 0.06680 -0.0469 0.0816 1.0000
16.250 1.4731 0.07598 0.07042 -0.0469 0.0782 1.0000
16.500 1.4748 0.07876 0.07328 -0.0470 0.0752 1.0000
16.750 1.4729 0.08198 0.07653 -0.0471 0.0716 1.0000
17.000 1.4677 0.08566 0.08024 -0.0473 0.0681 1.0000
17.250 1.4699 0.08841 0.08305 -0.0475 0.0638 1.0000
17.500 1.4649 0.09214 0.08680 -0.0479 0.0590 1.0000
17.750 1.4619 0.09562 0.09027 -0.0483 0.0521 1.0000
18.000 1.4553 0.09960 0.09423 -0.0488 0.0439 1.0000
18.250 1.4469 0.10385 0.09845 -0.0494 0.0360 1.0000
18.500 1.4383 0.10822 0.10281 -0.0502 0.0310 1.0000
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Polar data table (+)
Polar graphs
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