FX 61-147 AIRFOIL (fx61147-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 61-147 AIRFOIL (fx61147-il) Reynolds number: 50,000 Max Cl/Cd: 28.68 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx61147-il-50000-n5.txt Download as CSV file: xf-fx61147-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 61-147 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3587 0.10265 0.09587 -0.0491 1.0000 0.0459
-9.750 -0.3659 0.09781 0.09113 -0.0507 1.0000 0.0448
-9.500 -0.3771 0.09210 0.08557 -0.0532 1.0000 0.0435
-9.000 -0.4489 0.07951 0.07299 -0.0597 1.0000 0.0401
-8.750 -0.4674 0.07690 0.07045 -0.0580 1.0000 0.0399
-8.500 -0.4868 0.07429 0.06789 -0.0563 1.0000 0.0397
-8.250 -0.5041 0.07148 0.06508 -0.0548 1.0000 0.0396
-8.000 -0.5192 0.06864 0.06219 -0.0532 1.0000 0.0394
-7.750 -0.5310 0.06579 0.05926 -0.0516 1.0000 0.0393
-7.500 -0.5404 0.06279 0.05611 -0.0502 1.0000 0.0392
-7.250 -0.5455 0.05984 0.05299 -0.0489 1.0000 0.0391
-7.000 -0.5449 0.05654 0.04941 -0.0485 0.9993 0.0391
-6.750 -0.5174 0.05166 0.04393 -0.0531 0.9909 0.0393
-6.500 -0.4871 0.04749 0.03911 -0.0570 0.9820 0.0406
-6.250 -0.4554 0.04433 0.03578 -0.0603 0.9743 0.0435
-6.000 -0.4227 0.04148 0.03252 -0.0628 0.9652 0.0460
-5.750 -0.3888 0.03877 0.02936 -0.0645 0.9564 0.0477
-5.500 -0.3499 0.03666 0.02668 -0.0664 0.9490 0.0517
-5.250 -0.3203 0.03479 0.02480 -0.0668 0.9390 0.0560
-5.000 -0.2881 0.03343 0.02327 -0.0667 0.9299 0.0598
-4.750 -0.2534 0.03227 0.02192 -0.0670 0.9217 0.0669
-4.500 -0.2252 0.03113 0.02077 -0.0670 0.9105 0.0750
-4.250 -0.1951 0.02990 0.01949 -0.0678 0.8998 0.0866
-4.000 -0.1581 0.02829 0.01794 -0.0704 0.8917 0.1106
-3.750 -0.1299 0.02541 0.01622 -0.0737 0.8801 0.2513
-3.500 -0.1210 0.02574 0.01813 -0.0668 0.8677 0.5617
-3.250 -0.0986 0.02746 0.01965 -0.0623 0.8559 0.6501
-3.000 -0.0845 0.02935 0.02143 -0.0545 0.8457 0.7066
-2.750 -0.0625 0.02976 0.02158 -0.0513 0.8347 0.7334
-2.500 -0.0344 0.02950 0.02101 -0.0514 0.8231 0.7459
-2.250 -0.0041 0.02922 0.02046 -0.0513 0.8131 0.7550
-2.000 0.0313 0.02884 0.01978 -0.0526 0.8044 0.7644
-1.750 0.0588 0.02856 0.01925 -0.0529 0.7927 0.7738
-1.500 0.0877 0.02827 0.01875 -0.0529 0.7823 0.7811
-1.250 0.1249 0.02788 0.01810 -0.0550 0.7740 0.7896
-1.000 0.1491 0.02768 0.01774 -0.0542 0.7623 0.7961
-0.750 0.1786 0.02747 0.01733 -0.0551 0.7516 0.8039
-0.500 0.2134 0.02712 0.01679 -0.0560 0.7438 0.8095
-0.250 0.2377 0.02703 0.01656 -0.0560 0.7321 0.8165
0.000 0.2641 0.02689 0.01629 -0.0559 0.7217 0.8223
0.250 0.2995 0.02664 0.01587 -0.0573 0.7140 0.8282
0.500 0.3223 0.02665 0.01579 -0.0570 0.7028 0.8345
0.750 0.3483 0.02659 0.01563 -0.0569 0.6933 0.8400
1.000 0.3811 0.02649 0.01540 -0.0581 0.6852 0.8459
1.250 0.4026 0.02656 0.01543 -0.0574 0.6750 0.8513
1.500 0.4333 0.02650 0.01528 -0.0581 0.6671 0.8568
1.750 0.4583 0.02661 0.01535 -0.0582 0.6577 0.8624
2.000 0.4828 0.02668 0.01540 -0.0579 0.6491 0.8676
2.250 0.5125 0.02671 0.01537 -0.0586 0.6411 0.8731
2.500 0.5343 0.02694 0.01560 -0.0581 0.6320 0.8784
2.750 0.5661 0.02691 0.01554 -0.0589 0.6250 0.8835
3.000 0.5857 0.02727 0.01593 -0.0583 0.6155 0.8896
3.250 0.6191 0.02722 0.01585 -0.0593 0.6093 0.8943
3.500 0.6354 0.02766 0.01636 -0.0581 0.5997 0.9007
3.750 0.6666 0.02776 0.01647 -0.0589 0.5931 0.9061
4.000 0.6846 0.02819 0.01700 -0.0580 0.5843 0.9124
4.250 0.7147 0.02837 0.01719 -0.0588 0.5777 0.9185
4.500 0.7335 0.02885 0.01781 -0.0580 0.5691 0.9254
4.750 0.7639 0.02907 0.01807 -0.0588 0.5627 0.9319
5.000 0.7836 0.02963 0.01876 -0.0583 0.5540 0.9398
5.250 0.8142 0.02992 0.01913 -0.0593 0.5474 0.9477
5.500 0.8369 0.03054 0.01992 -0.0594 0.5388 0.9575
5.750 0.8680 0.03097 0.02047 -0.0607 0.5315 0.9691
6.000 0.8937 0.03158 0.02123 -0.0615 0.5232 1.0000
6.250 0.9190 0.03228 0.02207 -0.0621 0.5158 1.0000
6.500 0.9439 0.03302 0.02295 -0.0627 0.5081 1.0000
6.750 0.9676 0.03387 0.02394 -0.0632 0.5006 1.0000
7.000 0.9931 0.03463 0.02488 -0.0638 0.4929 1.0000
7.250 1.0136 0.03568 0.02610 -0.0640 0.4852 1.0000
7.500 1.0398 0.03644 0.02702 -0.0647 0.4777 1.0000
7.750 1.0554 0.03775 0.02852 -0.0643 0.4696 1.0000
8.000 1.0833 0.03843 0.02937 -0.0651 0.4624 1.0000
8.250 1.0906 0.04012 0.03129 -0.0639 0.4535 1.0000
8.500 1.1255 0.04039 0.03173 -0.0651 0.4467 1.0000
8.750 1.1200 0.04264 0.03418 -0.0627 0.4368 1.0000
9.000 1.1681 0.04197 0.03368 -0.0648 0.4299 1.0000
9.250 1.1549 0.04464 0.03655 -0.0617 0.4193 1.0000
9.500 1.1576 0.04656 0.03864 -0.0603 0.4097 1.0000
9.750 1.2055 0.04532 0.03764 -0.0615 0.4013 1.0000
10.000 1.1772 0.04938 0.04185 -0.0584 0.3903 1.0000
10.250 1.1725 0.05200 0.04464 -0.0571 0.3798 1.0000
10.500 1.2133 0.05048 0.04332 -0.0570 0.3697 1.0000
10.750 1.2204 0.05178 0.04480 -0.0559 0.3581 1.0000
11.000 1.1912 0.05700 0.05015 -0.0548 0.3464 1.0000
11.250 1.1817 0.06054 0.05383 -0.0545 0.3341 1.0000
11.500 1.1865 0.06240 0.05585 -0.0540 0.3213 1.0000
11.750 1.1928 0.06400 0.05761 -0.0536 0.3077 1.0000
12.000 1.1968 0.06596 0.05976 -0.0533 0.2935 1.0000
12.250 1.1979 0.06838 0.06232 -0.0532 0.2788 1.0000
12.500 1.1963 0.07123 0.06530 -0.0534 0.2628 1.0000
12.750 1.1996 0.07327 0.06744 -0.0534 0.2450 1.0000
13.000 1.2029 0.07531 0.06950 -0.0534 0.2254 1.0000
13.250 1.1946 0.07956 0.07382 -0.0543 0.2073 1.0000
13.500 1.1938 0.08256 0.07679 -0.0548 0.1873 1.0000
13.750 1.1904 0.08616 0.08032 -0.0556 0.1689 1.0000
14.000 1.1851 0.09026 0.08437 -0.0566 0.1519 1.0000
14.250 1.1804 0.09437 0.08838 -0.0577 0.1370 1.0000
14.500 1.1753 0.09869 0.09263 -0.0590 0.1239 1.0000
14.750 1.1705 0.10310 0.09698 -0.0604 0.1123 1.0000
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