FX 61-140 AIRFOIL (fx61140-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 61-140 AIRFOIL (fx61140-il) Reynolds number: 50,000 Max Cl/Cd: 31.17 at α=9.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx61140-il-50000-n5.txt Download as CSV file: xf-fx61140-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 61-140 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4062 0.10233 0.09541 -0.0438 1.0000 0.0407
-10.000 -0.4103 0.09724 0.09040 -0.0460 1.0000 0.0404
-9.750 -0.4159 0.09185 0.08508 -0.0485 1.0000 0.0399
-9.500 -0.4247 0.08639 0.07969 -0.0511 1.0000 0.0392
-9.250 -0.4384 0.08114 0.07450 -0.0537 1.0000 0.0386
-9.000 -0.4555 0.07647 0.06986 -0.0554 1.0000 0.0377
-8.750 -0.4772 0.07246 0.06588 -0.0558 1.0000 0.0372
-8.500 -0.5004 0.06923 0.06266 -0.0549 1.0000 0.0364
-8.250 -0.5179 0.06571 0.05909 -0.0546 1.0000 0.0360
-8.000 -0.5305 0.06245 0.05572 -0.0537 1.0000 0.0360
-7.750 -0.5387 0.05927 0.05238 -0.0527 1.0000 0.0362
-7.500 -0.5429 0.05613 0.04904 -0.0516 1.0000 0.0364
-7.250 -0.5429 0.05302 0.04568 -0.0506 1.0000 0.0366
-7.000 -0.5392 0.04991 0.04228 -0.0496 1.0000 0.0368
-6.750 -0.5316 0.04690 0.03893 -0.0487 1.0000 0.0369
-6.500 -0.5206 0.04408 0.03577 -0.0478 1.0000 0.0371
-6.250 -0.5068 0.04148 0.03282 -0.0469 1.0000 0.0376
-6.000 -0.4912 0.03922 0.03017 -0.0458 1.0000 0.0382
-5.750 -0.4745 0.03725 0.02789 -0.0445 1.0000 0.0394
-5.500 -0.4417 0.03541 0.02557 -0.0456 0.9949 0.0428
-5.250 -0.4058 0.03338 0.02350 -0.0470 0.9865 0.0469
-5.000 -0.3705 0.03200 0.02198 -0.0473 0.9769 0.0508
-4.750 -0.3362 0.03080 0.02061 -0.0478 0.9661 0.0582
-4.500 -0.3025 0.02949 0.01921 -0.0492 0.9540 0.0679
-4.250 -0.2683 0.02790 0.01760 -0.0515 0.9415 0.0853
-3.750 -0.2178 0.02441 0.01712 -0.0515 0.9162 0.5550
-3.500 -0.1987 0.02737 0.01997 -0.0444 0.9007 0.6598
-3.250 -0.1797 0.02928 0.02168 -0.0376 0.8875 0.7058
-3.000 -0.1446 0.02918 0.02117 -0.0381 0.8764 0.7211
-2.750 -0.1117 0.02893 0.02058 -0.0387 0.8636 0.7323
-2.500 -0.0775 0.02860 0.01994 -0.0400 0.8510 0.7429
-2.250 -0.0425 0.02825 0.01929 -0.0416 0.8385 0.7531
-2.000 -0.0095 0.02794 0.01871 -0.0422 0.8263 0.7602
-1.750 0.0251 0.02758 0.01809 -0.0439 0.8141 0.7690
-1.500 0.0592 0.02726 0.01754 -0.0448 0.8027 0.7754
-1.250 0.0921 0.02696 0.01699 -0.0462 0.7904 0.7831
-1.000 0.1210 0.02672 0.01658 -0.0463 0.7775 0.7891
-0.750 0.1508 0.02652 0.01620 -0.0473 0.7648 0.7964
-0.500 0.1789 0.02633 0.01585 -0.0472 0.7527 0.8018
-0.250 0.2087 0.02618 0.01554 -0.0481 0.7410 0.8084
0.000 0.2386 0.02601 0.01522 -0.0485 0.7303 0.8137
0.250 0.2662 0.02590 0.01500 -0.0488 0.7192 0.8193
0.500 0.2923 0.02587 0.01486 -0.0491 0.7075 0.8252
0.750 0.3182 0.02581 0.01473 -0.0489 0.6970 0.8301
1.000 0.3483 0.02575 0.01457 -0.0497 0.6877 0.8355
1.250 0.3734 0.02577 0.01454 -0.0496 0.6772 0.8406
1.500 0.3979 0.02581 0.01455 -0.0494 0.6671 0.8456
1.750 0.4276 0.02584 0.01450 -0.0502 0.6584 0.8511
2.000 0.4515 0.02591 0.01457 -0.0499 0.6487 0.8558
2.250 0.4760 0.02602 0.01470 -0.0497 0.6394 0.8609
2.500 0.5070 0.02609 0.01471 -0.0507 0.6315 0.8661
2.750 0.5274 0.02627 0.01495 -0.0499 0.6218 0.8708
3.000 0.5542 0.02640 0.01512 -0.0500 0.6137 0.8758
3.250 0.5801 0.02660 0.01535 -0.0503 0.6051 0.8809
3.500 0.6027 0.02682 0.01564 -0.0498 0.5967 0.8856
3.750 0.6309 0.02698 0.01582 -0.0502 0.5893 0.8906
4.000 0.6522 0.02735 0.01633 -0.0498 0.5805 0.8959
4.250 0.6814 0.02746 0.01648 -0.0502 0.5739 0.9006
4.500 0.7012 0.02795 0.01710 -0.0497 0.5647 0.9063
4.750 0.7295 0.02812 0.01734 -0.0500 0.5581 0.9113
5.000 0.7490 0.02861 0.01803 -0.0494 0.5492 0.9172
5.250 0.7750 0.02894 0.01847 -0.0496 0.5419 0.9228
5.500 0.7974 0.02937 0.01906 -0.0493 0.5338 0.9290
5.750 0.8212 0.02986 0.01971 -0.0493 0.5260 0.9354
6.000 0.8469 0.03026 0.02031 -0.0495 0.5184 0.9419
6.250 0.8684 0.03092 0.02118 -0.0494 0.5102 0.9495
6.500 0.8984 0.03127 0.02169 -0.0502 0.5030 0.9570
6.750 0.9190 0.03216 0.02285 -0.0503 0.4940 0.9670
7.000 0.9561 0.03236 0.02325 -0.0520 0.4872 0.9786
7.250 0.9732 0.03351 0.02470 -0.0520 0.4770 1.0000
7.500 0.9989 0.03431 0.02572 -0.0526 0.4684 1.0000
7.750 1.0288 0.03486 0.02649 -0.0536 0.4599 1.0000
8.000 1.0464 0.03611 0.02804 -0.0536 0.4497 1.0000
8.250 1.0733 0.03675 0.02892 -0.0541 0.4400 1.0000
8.500 1.1083 0.03672 0.02917 -0.0551 0.4297 1.0000
8.750 1.1280 0.03740 0.03014 -0.0547 0.4165 1.0000
9.000 1.1513 0.03763 0.03061 -0.0544 0.4020 1.0000
9.250 1.1688 0.03790 0.03113 -0.0535 0.3850 1.0000
9.500 1.1783 0.03855 0.03203 -0.0518 0.3664 1.0000
9.750 1.1927 0.03826 0.03184 -0.0500 0.3441 1.0000
10.000 1.1893 0.03979 0.03358 -0.0478 0.3223 1.0000
10.250 1.1891 0.04120 0.03510 -0.0462 0.2967 1.0000
10.500 1.1869 0.04324 0.03722 -0.0452 0.2695 1.0000
10.750 1.1823 0.04595 0.04005 -0.0449 0.2403 1.0000
11.000 1.1758 0.04921 0.04325 -0.0449 0.2081 1.0000
11.250 1.1661 0.05315 0.04700 -0.0454 0.1775 1.0000
11.500 1.1538 0.05778 0.05146 -0.0463 0.1515 1.0000
11.750 1.1411 0.06274 0.05626 -0.0475 0.1311 1.0000
12.000 1.1290 0.06782 0.06121 -0.0489 0.1151 1.0000
12.250 1.1190 0.07280 0.06610 -0.0502 0.1022 1.0000
12.500 1.1113 0.07753 0.07077 -0.0514 0.0920 1.0000
12.750 1.1047 0.08217 0.07532 -0.0526 0.0831 1.0000
13.000 1.1003 0.08672 0.07990 -0.0540 0.0740 1.0000
13.250 1.0982 0.09103 0.08429 -0.0551 0.0660 1.0000
13.500 1.0966 0.09516 0.08831 -0.0562 0.0596 1.0000
13.750 1.0952 0.09977 0.09314 -0.0579 0.0525 1.0000
14.000 1.0928 0.10429 0.09762 -0.0597 0.0471 1.0000
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