GOE 425 AIRFOIL (goe425-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 425 AIRFOIL (goe425-il) Reynolds number: 500,000 Max Cl/Cd: 108.37 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe425-il-500000-n5.txt Download as CSV file: xf-goe425-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5856 0.04423 0.04017 -0.0881 0.7133 0.0238
-11.000 -0.6045 0.03991 0.03553 -0.0894 0.7074 0.0239
-10.750 -0.6082 0.03644 0.03174 -0.0896 0.7013 0.0242
-10.500 -0.6038 0.03364 0.02860 -0.0894 0.6953 0.0246
-10.250 -0.5946 0.03116 0.02578 -0.0889 0.6897 0.0250
-10.000 -0.5812 0.02910 0.02341 -0.0884 0.6834 0.0252
-9.750 -0.5645 0.02747 0.02147 -0.0879 0.6773 0.0255
-9.500 -0.5452 0.02615 0.01990 -0.0874 0.6717 0.0256
-9.250 -0.5252 0.02471 0.01828 -0.0870 0.6658 0.0258
-9.000 -0.5035 0.02357 0.01701 -0.0866 0.6600 0.0260
-8.750 -0.4804 0.02266 0.01599 -0.0864 0.6546 0.0262
-8.500 -0.4565 0.02187 0.01510 -0.0861 0.6485 0.0264
-8.250 -0.4324 0.02115 0.01428 -0.0858 0.6425 0.0266
-8.000 -0.4076 0.02050 0.01354 -0.0856 0.6366 0.0269
-7.750 -0.3825 0.01992 0.01286 -0.0853 0.6298 0.0272
-7.500 -0.3574 0.01934 0.01217 -0.0851 0.6234 0.0275
-7.250 -0.3319 0.01870 0.01144 -0.0848 0.6169 0.0278
-7.000 -0.3064 0.01809 0.01072 -0.0846 0.6105 0.0280
-6.750 -0.2807 0.01751 0.01003 -0.0843 0.6049 0.0283
-6.500 -0.2547 0.01696 0.00940 -0.0841 0.5987 0.0286
-6.250 -0.2286 0.01646 0.00881 -0.0839 0.5927 0.0288
-6.000 -0.2024 0.01600 0.00826 -0.0836 0.5874 0.0291
-5.750 -0.1760 0.01556 0.00776 -0.0834 0.5815 0.0293
-5.500 -0.1496 0.01518 0.00729 -0.0832 0.5757 0.0296
-5.250 -0.1230 0.01483 0.00687 -0.0830 0.5705 0.0298
-5.000 -0.0962 0.01450 0.00650 -0.0828 0.5654 0.0300
-4.750 -0.0705 0.01400 0.00596 -0.0825 0.5607 0.0304
-4.250 -0.0173 0.01338 0.00531 -0.0822 0.5525 0.0314
-4.000 0.0098 0.01313 0.00504 -0.0820 0.5483 0.0318
-3.750 0.0367 0.01289 0.00476 -0.0819 0.5440 0.0323
-3.500 0.0636 0.01268 0.00450 -0.0817 0.5400 0.0327
-3.250 0.0909 0.01247 0.00426 -0.0816 0.5367 0.0332
-3.000 0.1185 0.01227 0.00405 -0.0815 0.5335 0.0337
-2.750 0.1460 0.01210 0.00385 -0.0815 0.5301 0.0342
-2.500 0.1735 0.01196 0.00367 -0.0814 0.5266 0.0346
-2.250 0.2008 0.01181 0.00348 -0.0813 0.5233 0.0352
-2.000 0.2284 0.01166 0.00332 -0.0812 0.5204 0.0360
-1.750 0.2564 0.01153 0.00319 -0.0813 0.5177 0.0370
-1.500 0.2844 0.01144 0.00309 -0.0813 0.5147 0.0383
-1.250 0.3124 0.01137 0.00300 -0.0813 0.5115 0.0397
-1.000 0.3403 0.01130 0.00291 -0.0813 0.5085 0.0413
-0.750 0.3680 0.01125 0.00283 -0.0812 0.5057 0.0436
-0.500 0.3961 0.01119 0.00276 -0.0812 0.5031 0.0471
-0.250 0.4236 0.01097 0.00270 -0.0813 0.5003 0.0863
0.000 0.4517 0.01092 0.00269 -0.0813 0.4974 0.1087
0.250 0.4796 0.01086 0.00267 -0.0814 0.4943 0.1247
0.500 0.5052 0.01040 0.00262 -0.0813 0.4914 0.2634
0.750 0.5308 0.01005 0.00264 -0.0811 0.4887 0.3956
1.000 0.5579 0.00993 0.00272 -0.0811 0.4863 0.4664
1.250 0.5858 0.00988 0.00279 -0.0811 0.4838 0.5041
1.500 0.6133 0.00984 0.00286 -0.0811 0.4809 0.5421
1.750 0.6405 0.00979 0.00294 -0.0810 0.4780 0.5816
2.000 0.6678 0.00977 0.00301 -0.0809 0.4754 0.6126
2.500 0.7222 0.00982 0.00315 -0.0807 0.4704 0.6611
3.000 0.7765 0.00974 0.00332 -0.0805 0.4649 0.7248
3.250 0.8010 0.00959 0.00343 -0.0797 0.4621 0.7978
3.500 0.8511 0.00945 0.00360 -0.0843 0.4590 0.9680
3.750 0.8892 0.00958 0.00369 -0.0867 0.4555 0.9968
4.000 0.9184 0.00969 0.00379 -0.0871 0.4521 1.0000
4.250 0.9445 0.00978 0.00389 -0.0868 0.4483 1.0000
4.500 0.9705 0.00989 0.00400 -0.0865 0.4447 1.0000
4.750 0.9961 0.01002 0.00411 -0.0861 0.4412 1.0000
5.000 1.0215 0.01017 0.00422 -0.0858 0.4374 1.0000
5.250 1.0478 0.01027 0.00436 -0.0856 0.4332 1.0000
5.500 1.0736 0.01039 0.00449 -0.0853 0.4290 1.0000
5.750 1.0991 0.01054 0.00463 -0.0850 0.4250 1.0000
6.000 1.1244 0.01070 0.00478 -0.0846 0.4206 1.0000
6.250 1.1502 0.01082 0.00493 -0.0844 0.4150 1.0000
6.500 1.1750 0.01099 0.00509 -0.0840 0.4088 1.0000
6.750 1.2001 0.01117 0.00527 -0.0836 0.4035 1.0000
7.000 1.2253 0.01133 0.00546 -0.0833 0.3979 1.0000
7.250 1.2490 0.01156 0.00566 -0.0827 0.3910 1.0000
7.500 1.2734 0.01175 0.00587 -0.0823 0.3827 1.0000
7.750 1.2964 0.01201 0.00611 -0.0817 0.3756 1.0000
8.000 1.3207 0.01222 0.00635 -0.0813 0.3694 1.0000
8.250 1.3427 0.01252 0.00664 -0.0805 0.3609 1.0000
8.500 1.3652 0.01280 0.00693 -0.0798 0.3521 1.0000
8.750 1.3857 0.01317 0.00727 -0.0789 0.3433 1.0000
9.000 1.4062 0.01353 0.00763 -0.0779 0.3325 1.0000
9.250 1.4252 0.01394 0.00803 -0.0767 0.3218 1.0000
9.500 1.4420 0.01443 0.00849 -0.0752 0.3108 1.0000
9.750 1.4546 0.01502 0.00904 -0.0731 0.2965 1.0000
10.000 1.4647 0.01575 0.00971 -0.0707 0.2783 1.0000
10.250 1.4697 0.01679 0.01065 -0.0678 0.2540 1.0000
10.500 1.4673 0.01836 0.01207 -0.0645 0.2221 1.0000
10.750 1.4579 0.02062 0.01415 -0.0611 0.1875 1.0000
11.000 1.4540 0.02284 0.01629 -0.0589 0.1687 1.0000
11.250 1.4559 0.02483 0.01827 -0.0576 0.1581 1.0000
11.500 1.4578 0.02696 0.02040 -0.0564 0.1495 1.0000
11.750 1.4619 0.02896 0.02244 -0.0555 0.1418 1.0000
12.000 1.4635 0.03123 0.02472 -0.0546 0.1350 1.0000
12.250 1.4672 0.03333 0.02686 -0.0539 0.1277 1.0000
12.500 1.4669 0.03580 0.02934 -0.0530 0.1207 1.0000
12.750 1.4676 0.03821 0.03178 -0.0522 0.1132 1.0000
13.000 1.4656 0.04089 0.03448 -0.0514 0.1058 1.0000
13.250 1.4612 0.04385 0.03744 -0.0506 0.0979 1.0000
13.500 1.4587 0.04671 0.04031 -0.0499 0.0917 1.0000
13.750 1.4547 0.04979 0.04341 -0.0494 0.0865 1.0000
14.000 1.4547 0.05252 0.04618 -0.0490 0.0828 1.0000
14.250 1.4535 0.05544 0.04914 -0.0486 0.0793 1.0000
14.500 1.4500 0.05864 0.05237 -0.0483 0.0758 1.0000
14.750 1.4514 0.06132 0.05511 -0.0481 0.0728 1.0000
15.000 1.4513 0.06422 0.05806 -0.0480 0.0696 1.0000
15.250 1.4488 0.06743 0.06130 -0.0479 0.0667 1.0000
15.500 1.4501 0.07018 0.06411 -0.0478 0.0643 1.0000
15.750 1.4508 0.07306 0.06705 -0.0478 0.0613 1.0000
16.000 1.4497 0.07614 0.07016 -0.0478 0.0579 1.0000
16.250 1.4492 0.07923 0.07330 -0.0479 0.0546 1.0000
16.500 1.4477 0.08240 0.07649 -0.0480 0.0502 1.0000
16.750 1.4454 0.08573 0.07984 -0.0482 0.0455 1.0000
17.000 1.4419 0.08922 0.08333 -0.0484 0.0398 1.0000
17.250 1.4364 0.09303 0.08715 -0.0488 0.0339 1.0000
17.500 1.4305 0.09689 0.09100 -0.0492 0.0280 1.0000
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