GOE 512 AIRFOIL (goe512-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 512 AIRFOIL (goe512-il) Reynolds number: 200,000 Max Cl/Cd: 60.9 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe512-il-200000-n5.txt Download as CSV file: xf-goe512-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 512 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4761 0.04066 0.03632 -0.0935 0.9471 0.0197
-9.500 -0.4635 0.04033 0.03603 -0.0915 0.9402 0.0201
-9.250 -0.4506 0.03810 0.03362 -0.0912 0.9349 0.0206
-9.000 -0.4312 0.03585 0.03111 -0.0919 0.9318 0.0214
-8.750 -0.4349 0.03324 0.02814 -0.0879 0.9218 0.0221
-8.500 -0.4235 0.02981 0.02410 -0.0866 0.9173 0.0231
-8.250 -0.4166 0.02780 0.02171 -0.0834 0.9094 0.0238
-8.000 -0.3927 0.02684 0.02068 -0.0829 0.9043 0.0245
-7.750 -0.3631 0.02575 0.01944 -0.0835 0.9012 0.0255
-7.500 -0.3497 0.02484 0.01833 -0.0808 0.8918 0.0268
-7.250 -0.3241 0.02337 0.01651 -0.0804 0.8875 0.0285
-7.000 -0.3008 0.02280 0.01593 -0.0795 0.8814 0.0297
-6.750 -0.2782 0.02206 0.01507 -0.0784 0.8743 0.0312
-6.500 -0.2464 0.02092 0.01365 -0.0790 0.8706 0.0334
-6.250 -0.2275 0.02038 0.01308 -0.0771 0.8605 0.0350
-6.000 -0.1926 0.01971 0.01231 -0.0783 0.8555 0.0375
-5.750 -0.1690 0.01908 0.01148 -0.0772 0.8455 0.0398
-5.500 -0.1331 0.01836 0.01074 -0.0788 0.8402 0.0423
-5.250 -0.1058 0.01792 0.01023 -0.0785 0.8313 0.0450
-5.000 -0.0672 0.01727 0.00942 -0.0804 0.8246 0.0482
-4.750 -0.0369 0.01676 0.00891 -0.0809 0.8148 0.0512
-4.500 0.0049 0.01628 0.00830 -0.0836 0.8068 0.0554
-4.250 0.0333 0.01581 0.00775 -0.0835 0.7951 0.0582
-4.000 0.0652 0.01534 0.00725 -0.0843 0.7841 0.0616
-3.750 0.0988 0.01499 0.00679 -0.0853 0.7719 0.0661
-3.500 0.1268 0.01466 0.00638 -0.0851 0.7577 0.0699
-3.250 0.1537 0.01435 0.00600 -0.0847 0.7425 0.0750
-3.000 0.1809 0.01415 0.00568 -0.0844 0.7271 0.0811
-2.750 0.2069 0.01388 0.00538 -0.0839 0.7120 0.0892
-2.500 0.2325 0.01366 0.00514 -0.0833 0.6973 0.1026
-2.250 0.2571 0.01341 0.00495 -0.0825 0.6828 0.1385
-2.000 0.2803 0.01327 0.00494 -0.0815 0.6677 0.1864
-1.750 0.3034 0.01341 0.00503 -0.0803 0.6513 0.2249
-1.500 0.3264 0.01357 0.00503 -0.0791 0.6357 0.2432
-1.250 0.3487 0.01375 0.00505 -0.0777 0.6209 0.2566
-1.000 0.3699 0.01390 0.00508 -0.0761 0.6062 0.2668
-0.750 0.3906 0.01401 0.00508 -0.0745 0.5913 0.2748
-0.500 0.4106 0.01411 0.00507 -0.0727 0.5756 0.2819
-0.250 0.4303 0.01419 0.00506 -0.0709 0.5599 0.2890
0.000 0.4494 0.01427 0.00505 -0.0690 0.5442 0.2964
0.250 0.4680 0.01433 0.00502 -0.0671 0.5280 0.3031
0.500 0.4871 0.01437 0.00500 -0.0652 0.5139 0.3084
0.750 0.5055 0.01445 0.00498 -0.0632 0.5006 0.3130
1.250 0.5413 0.01455 0.00496 -0.0590 0.4774 0.3198
1.500 0.5593 0.01462 0.00497 -0.0570 0.4678 0.3243
1.750 0.5779 0.01471 0.00501 -0.0551 0.4588 0.3292
2.000 0.5965 0.01479 0.00505 -0.0532 0.4510 0.3327
2.250 0.6149 0.01486 0.00511 -0.0513 0.4432 0.3365
2.500 0.6335 0.01498 0.00519 -0.0495 0.4362 0.3397
2.750 0.6530 0.01509 0.00528 -0.0478 0.4291 0.3435
3.000 0.6717 0.01525 0.00539 -0.0460 0.4224 0.3474
3.250 0.6910 0.01536 0.00550 -0.0444 0.4158 0.3514
3.500 0.7100 0.01550 0.00564 -0.0427 0.4090 0.3561
3.750 0.7286 0.01568 0.00578 -0.0410 0.4025 0.3623
4.000 0.7481 0.01578 0.00595 -0.0394 0.3955 0.3724
4.250 0.7656 0.01584 0.00613 -0.0375 0.3887 0.4132
4.750 0.9627 0.01635 0.00784 -0.0687 0.3631 0.9857
5.000 0.9970 0.01671 0.00814 -0.0705 0.3544 0.9929
5.250 1.0378 0.01704 0.00846 -0.0737 0.3447 0.9991
5.500 1.0545 0.01733 0.00870 -0.0718 0.3375 1.0000
5.750 1.0681 0.01755 0.00893 -0.0692 0.3300 1.0000
6.000 1.0793 0.01783 0.00917 -0.0662 0.3229 1.0000
6.250 1.0922 0.01810 0.00943 -0.0635 0.3153 1.0000
6.500 1.1037 0.01841 0.00973 -0.0606 0.3083 1.0000
6.750 1.1163 0.01874 0.01004 -0.0580 0.3016 1.0000
7.000 1.1286 0.01909 0.01037 -0.0553 0.2951 1.0000
7.250 1.1401 0.01949 0.01073 -0.0526 0.2898 1.0000
7.500 1.1541 0.01985 0.01112 -0.0504 0.2847 1.0000
7.750 1.1671 0.02026 0.01153 -0.0480 0.2800 1.0000
8.000 1.1790 0.02072 0.01196 -0.0455 0.2760 1.0000
8.250 1.1931 0.02115 0.01241 -0.0434 0.2721 1.0000
8.500 1.2070 0.02159 0.01289 -0.0413 0.2678 1.0000
8.750 1.2196 0.02209 0.01339 -0.0391 0.2637 1.0000
9.000 1.2311 0.02265 0.01393 -0.0368 0.2600 1.0000
9.250 1.2452 0.02315 0.01447 -0.0349 0.2565 1.0000
9.500 1.2588 0.02366 0.01505 -0.0330 0.2525 1.0000
9.750 1.2716 0.02423 0.01564 -0.0311 0.2489 1.0000
10.000 1.2835 0.02486 0.01628 -0.0291 0.2456 1.0000
10.250 1.2959 0.02553 0.01693 -0.0272 0.2429 1.0000
10.500 1.3101 0.02610 0.01761 -0.0256 0.2402 1.0000
10.750 1.3240 0.02670 0.01830 -0.0240 0.2377 1.0000
11.000 1.3373 0.02735 0.01902 -0.0224 0.2351 1.0000
11.250 1.3498 0.02805 0.01978 -0.0208 0.2326 1.0000
11.500 1.3617 0.02881 0.02058 -0.0191 0.2300 1.0000
11.750 1.3722 0.02967 0.02142 -0.0174 0.2265 1.0000
12.000 1.3818 0.03051 0.02241 -0.0157 0.2227 1.0000
12.250 1.3901 0.03145 0.02345 -0.0139 0.2182 1.0000
12.500 1.3981 0.03247 0.02452 -0.0122 0.2144 1.0000
12.750 1.4054 0.03358 0.02563 -0.0105 0.2108 1.0000
13.000 1.4127 0.03471 0.02691 -0.0090 0.2065 1.0000
13.250 1.4197 0.03592 0.02825 -0.0076 0.2021 1.0000
13.500 1.4235 0.03737 0.02974 -0.0060 0.1973 1.0000
13.750 1.4280 0.03885 0.03128 -0.0047 0.1932 1.0000
14.000 1.4337 0.04034 0.03294 -0.0036 0.1879 1.0000
14.250 1.4370 0.04205 0.03474 -0.0025 0.1832 1.0000
14.500 1.4395 0.04391 0.03667 -0.0015 0.1790 1.0000
14.750 1.4427 0.04584 0.03875 -0.0007 0.1721 1.0000
15.000 1.4411 0.04826 0.04122 0.0001 0.1660 1.0000
15.250 1.4423 0.05052 0.04360 0.0006 0.1580 1.0000
15.500 1.4359 0.05366 0.04678 0.0010 0.1474 1.0000
15.750 1.4282 0.05703 0.05019 0.0013 0.1393 1.0000
16.000 1.4208 0.06048 0.05370 0.0015 0.1321 1.0000
16.250 1.4082 0.06467 0.05794 0.0013 0.1245 1.0000
16.500 1.3961 0.06894 0.06227 0.0010 0.1181 1.0000
16.750 1.3818 0.07363 0.06703 0.0005 0.1117 1.0000
17.000 1.3637 0.07895 0.07241 -0.0004 0.1051 1.0000
17.250 1.3501 0.08382 0.07737 -0.0013 0.0996 1.0000
17.750 1.3106 0.09563 0.08933 -0.0041 0.0829 1.0000
18.000 1.2883 0.10209 0.09584 -0.0059 0.0742 1.0000
18.250 1.2676 0.10847 0.10230 -0.0078 0.0673 1.0000
18.500 1.2381 0.11635 0.11020 -0.0105 0.0575 1.0000
18.750 1.2157 0.12329 0.11720 -0.0129 0.0506 1.0000
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