GOE 601 AIRFOIL (goe601-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 601 AIRFOIL (goe601-il) Reynolds number: 100,000 Max Cl/Cd: 44.11 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe601-il-100000-n5.txt Download as CSV file: xf-goe601-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 601 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.6366 0.08901 0.08290 -0.0747 1.0000 0.0492
-14.500 -0.6874 0.07796 0.07165 -0.0811 1.0000 0.0489
-14.250 -0.7237 0.07042 0.06390 -0.0848 1.0000 0.0488
-14.000 -0.7544 0.06446 0.05774 -0.0872 1.0000 0.0489
-13.750 -0.7793 0.05976 0.05283 -0.0882 1.0000 0.0490
-13.500 -0.8008 0.05594 0.04880 -0.0881 1.0000 0.0492
-13.250 -0.8093 0.05348 0.04629 -0.0871 1.0000 0.0497
-13.000 -0.8163 0.05141 0.04417 -0.0856 1.0000 0.0502
-12.750 -0.8255 0.04940 0.04210 -0.0837 1.0000 0.0506
-12.500 -0.8357 0.04758 0.04020 -0.0812 1.0000 0.0510
-12.250 -0.8468 0.04596 0.03850 -0.0781 1.0000 0.0514
-12.000 -0.8592 0.04460 0.03706 -0.0743 1.0000 0.0519
-11.750 -0.8734 0.04346 0.03585 -0.0698 1.0000 0.0524
-11.500 -0.8902 0.04256 0.03487 -0.0643 1.0000 0.0528
-11.250 -0.8883 0.04121 0.03337 -0.0623 0.9967 0.0539
-11.000 -0.8694 0.03937 0.03125 -0.0632 0.9908 0.0554
-10.750 -0.8478 0.03767 0.02933 -0.0641 0.9852 0.0569
-10.500 -0.8238 0.03640 0.02805 -0.0651 0.9801 0.0582
-10.250 -0.8011 0.03521 0.02678 -0.0657 0.9740 0.0597
-10.000 -0.7756 0.03402 0.02546 -0.0668 0.9694 0.0620
-9.750 -0.7557 0.03289 0.02414 -0.0664 0.9624 0.0641
-9.500 -0.7294 0.03183 0.02307 -0.0674 0.9579 0.0662
-9.250 -0.7108 0.03097 0.02218 -0.0668 0.9507 0.0683
-9.000 -0.6863 0.03004 0.02115 -0.0671 0.9454 0.0711
-8.750 -0.6581 0.02911 0.02015 -0.0682 0.9419 0.0749
-8.500 -0.6449 0.02851 0.01953 -0.0662 0.9331 0.0780
-8.250 -0.6180 0.02774 0.01864 -0.0667 0.9288 0.0838
-8.000 -0.6005 0.02711 0.01800 -0.0655 0.9221 0.0890
-7.750 -0.5797 0.02644 0.01723 -0.0648 0.9162 0.0961
-7.500 -0.5522 0.02571 0.01643 -0.0654 0.9126 0.1053
-7.250 -0.5389 0.02514 0.01583 -0.0632 0.9050 0.1126
-7.000 -0.5150 0.02458 0.01516 -0.0629 0.9001 0.1224
-6.750 -0.4883 0.02380 0.01440 -0.0634 0.8969 0.1324
-6.500 -0.4747 0.02338 0.01396 -0.0611 0.8894 0.1400
-6.250 -0.4511 0.02283 0.01339 -0.0607 0.8848 0.1501
-6.000 -0.4228 0.02221 0.01282 -0.0613 0.8818 0.1643
-5.500 -0.3865 0.02127 0.01216 -0.0585 0.8701 0.2136
-5.250 -0.3591 0.02072 0.01178 -0.0588 0.8669 0.2557
-5.000 -0.3304 0.02027 0.01141 -0.0592 0.8639 0.2939
-4.750 -0.3188 0.02012 0.01131 -0.0563 0.8560 0.3185
-4.500 -0.2911 0.01978 0.01104 -0.0563 0.8524 0.3471
-4.250 -0.2601 0.01948 0.01080 -0.0569 0.8498 0.3745
-4.000 -0.2430 0.01944 0.01079 -0.0550 0.8433 0.3966
-3.750 -0.2190 0.01935 0.01071 -0.0542 0.8384 0.4207
-3.500 -0.1888 0.01921 0.01055 -0.0546 0.8352 0.4464
-3.250 -0.1556 0.01904 0.01034 -0.0555 0.8328 0.4718
-3.000 -0.1424 0.01916 0.01046 -0.0528 0.8252 0.4893
-2.750 -0.1156 0.01909 0.01035 -0.0525 0.8209 0.5067
-2.500 -0.0835 0.01893 0.01017 -0.0532 0.8179 0.5240
-2.250 -0.0489 0.01873 0.00997 -0.0543 0.8156 0.5422
-2.000 -0.0387 0.01893 0.01021 -0.0510 0.8073 0.5560
-1.750 -0.0108 0.01885 0.01015 -0.0509 0.8032 0.5724
-1.500 0.0222 0.01870 0.01003 -0.0517 0.8003 0.5903
-1.250 0.0575 0.01853 0.00989 -0.0529 0.7980 0.6098
-1.000 0.0646 0.01880 0.01023 -0.0490 0.7885 0.6250
-0.750 0.0977 0.01862 0.01007 -0.0497 0.7841 0.6448
-0.500 0.1383 0.01829 0.00975 -0.0516 0.7806 0.6654
-0.250 0.1486 0.01846 0.01000 -0.0482 0.7705 0.6824
0.000 0.1856 0.01818 0.00975 -0.0495 0.7654 0.7030
0.250 0.2116 0.01813 0.00975 -0.0489 0.7585 0.7225
0.500 0.2378 0.01806 0.00975 -0.0483 0.7508 0.7427
0.750 0.2792 0.01777 0.00950 -0.0503 0.7461 0.7651
1.000 0.2970 0.01788 0.00971 -0.0482 0.7363 0.7907
1.250 0.3388 0.01765 0.00955 -0.0502 0.7299 0.8202
1.500 0.3687 0.01769 0.00969 -0.0502 0.7201 0.8511
1.750 0.4158 0.01756 0.00958 -0.0534 0.7128 0.8754
2.000 0.4515 0.01767 0.00974 -0.0549 0.7035 0.8974
2.250 0.4964 0.01759 0.00965 -0.0580 0.6957 0.9138
2.500 0.5328 0.01769 0.00979 -0.0597 0.6850 0.9316
2.750 0.5779 0.01759 0.00967 -0.0629 0.6756 0.9451
3.000 0.6155 0.01764 0.00974 -0.0649 0.6632 0.9599
3.250 0.6537 0.01767 0.00979 -0.0671 0.6494 0.9738
3.500 0.6938 0.01766 0.00978 -0.0696 0.6344 0.9863
3.750 0.7358 0.01764 0.00975 -0.0726 0.6169 0.9980
4.000 0.7521 0.01765 0.00971 -0.0705 0.5996 1.0000
4.250 0.7626 0.01767 0.00966 -0.0672 0.5808 1.0000
4.500 0.7747 0.01771 0.00961 -0.0641 0.5603 1.0000
4.750 0.7839 0.01785 0.00967 -0.0605 0.5372 1.0000
5.000 0.7948 0.01802 0.00969 -0.0572 0.5116 1.0000
5.250 0.8037 0.01827 0.00979 -0.0536 0.4840 1.0000
5.500 0.8111 0.01858 0.00992 -0.0497 0.4578 1.0000
5.750 0.8174 0.01894 0.01014 -0.0457 0.4339 1.0000
6.000 0.8251 0.01934 0.01039 -0.0420 0.4139 1.0000
6.250 0.8346 0.01977 0.01070 -0.0388 0.3969 1.0000
6.500 0.8462 0.02023 0.01104 -0.0360 0.3828 1.0000
6.750 0.8597 0.02069 0.01143 -0.0336 0.3709 1.0000
7.000 0.8743 0.02119 0.01182 -0.0315 0.3601 1.0000
7.250 0.8897 0.02167 0.01227 -0.0295 0.3498 1.0000
7.500 0.9057 0.02219 0.01270 -0.0277 0.3403 1.0000
7.750 0.9200 0.02271 0.01323 -0.0256 0.3297 1.0000
8.000 0.9356 0.02326 0.01372 -0.0238 0.3204 1.0000
8.250 0.9495 0.02381 0.01426 -0.0218 0.3105 1.0000
8.500 0.9653 0.02436 0.01482 -0.0201 0.3022 1.0000
8.750 0.9801 0.02491 0.01541 -0.0183 0.2941 1.0000
9.000 0.9955 0.02549 0.01598 -0.0167 0.2866 1.0000
9.250 1.0084 0.02607 0.01665 -0.0147 0.2782 1.0000
9.500 1.0230 0.02669 0.01725 -0.0131 0.2713 1.0000
9.750 1.0356 0.02730 0.01801 -0.0112 0.2635 1.0000
10.000 1.0467 0.02799 0.01869 -0.0092 0.2557 1.0000
10.250 1.0556 0.02871 0.01955 -0.0070 0.2456 1.0000
10.500 1.0625 0.02955 0.02042 -0.0047 0.2349 1.0000
10.750 1.0685 0.03048 0.02140 -0.0025 0.2231 1.0000
11.000 1.0757 0.03144 0.02245 -0.0006 0.2102 1.0000
11.250 1.0814 0.03255 0.02360 0.0013 0.1950 1.0000
11.500 1.0859 0.03381 0.02488 0.0032 0.1776 1.0000
11.750 1.0890 0.03529 0.02632 0.0051 0.1526 1.0000
12.000 1.0858 0.03731 0.02817 0.0071 0.1193 1.0000
12.250 1.0773 0.03994 0.03053 0.0092 0.0902 1.0000
12.500 1.0719 0.04250 0.03298 0.0109 0.0777 1.0000
12.750 1.0689 0.04495 0.03545 0.0122 0.0709 1.0000
13.000 1.0639 0.04769 0.03821 0.0134 0.0663 1.0000
13.250 1.0616 0.05028 0.04091 0.0143 0.0630 1.0000
13.500 1.0567 0.05324 0.04396 0.0150 0.0605 1.0000
13.750 1.0502 0.05651 0.04731 0.0154 0.0587 1.0000
14.000 1.0438 0.05993 0.05083 0.0156 0.0572 1.0000
14.250 1.0387 0.06335 0.05440 0.0155 0.0559 1.0000
14.500 1.0324 0.06706 0.05825 0.0152 0.0547 1.0000
14.750 1.0262 0.07090 0.06221 0.0147 0.0538 1.0000
15.000 1.0194 0.07493 0.06634 0.0139 0.0529 1.0000
15.250 1.0137 0.07891 0.07041 0.0131 0.0521 1.0000
15.500 1.0087 0.08282 0.07440 0.0122 0.0512 1.0000
15.750 1.0056 0.08642 0.07803 0.0115 0.0504 1.0000
16.000 1.0068 0.08951 0.08123 0.0109 0.0495 1.0000
16.250 1.0091 0.09240 0.08421 0.0104 0.0484 1.0000
16.500 1.0117 0.09527 0.08718 0.0099 0.0473 1.0000
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