WORTMANN FX 60-126 AIRFOIL (fx60126-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 60-126 AIRFOIL (fx60126-il) Reynolds number: 50,000 Max Cl/Cd: 39.13 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx60126-il-50000-n5.txt Download as CSV file: xf-fx60126-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 60-126 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3807 0.10240 0.09507 -0.0450 1.0000 0.0473
-10.250 -0.3855 0.09757 0.09032 -0.0468 1.0000 0.0473
-10.000 -0.3927 0.09240 0.08525 -0.0489 1.0000 0.0472
-9.750 -0.4044 0.08641 0.07938 -0.0513 1.0000 0.0470
-9.500 -0.4204 0.08003 0.07310 -0.0541 1.0000 0.0463
-9.250 -0.4992 0.06605 0.05902 -0.0634 1.0000 0.0415
-9.000 -0.5228 0.06222 0.05521 -0.0644 1.0000 0.0414
-8.750 -0.5392 0.05852 0.05144 -0.0656 1.0000 0.0412
-8.500 -0.5546 0.05466 0.04736 -0.0666 1.0000 0.0414
-8.250 -0.5594 0.05140 0.04394 -0.0668 1.0000 0.0418
-8.000 -0.5563 0.04899 0.04146 -0.0664 1.0000 0.0429
-7.750 -0.5508 0.04640 0.03869 -0.0664 1.0000 0.0441
-7.500 -0.5420 0.04371 0.03574 -0.0665 1.0000 0.0455
-7.250 -0.5298 0.04093 0.03263 -0.0665 1.0000 0.0471
-7.000 -0.5147 0.03840 0.02969 -0.0664 1.0000 0.0489
-6.750 -0.4984 0.03647 0.02758 -0.0660 1.0000 0.0518
-6.500 -0.4809 0.03494 0.02593 -0.0657 1.0000 0.0562
-6.250 -0.4621 0.03325 0.02403 -0.0652 1.0000 0.0614
-6.000 -0.4424 0.03182 0.02246 -0.0650 1.0000 0.0693
-5.750 -0.4218 0.03042 0.02106 -0.0651 1.0000 0.0794
-5.500 -0.3856 0.02880 0.01942 -0.0684 0.9945 0.1008
-5.250 -0.3478 0.02730 0.01796 -0.0721 0.9883 0.1350
-5.000 -0.3080 0.02592 0.01678 -0.0760 0.9827 0.1810
-4.750 -0.2723 0.02500 0.01609 -0.0787 0.9756 0.2336
-4.500 -0.2336 0.02481 0.01606 -0.0815 0.9691 0.2971
-4.250 -0.2001 0.02495 0.01619 -0.0827 0.9604 0.3441
-4.000 -0.1629 0.02519 0.01627 -0.0846 0.9528 0.3829
-3.750 -0.1292 0.02546 0.01643 -0.0856 0.9438 0.4141
-3.500 -0.0957 0.02575 0.01660 -0.0864 0.9353 0.4417
-3.250 -0.0615 0.02596 0.01670 -0.0873 0.9270 0.4643
-3.000 -0.0302 0.02607 0.01670 -0.0878 0.9181 0.4835
-2.750 0.0062 0.02612 0.01660 -0.0893 0.9105 0.5029
-2.500 0.0362 0.02615 0.01651 -0.0897 0.9009 0.5193
-2.250 0.0750 0.02611 0.01634 -0.0916 0.8941 0.5357
-2.000 0.1038 0.02609 0.01623 -0.0918 0.8834 0.5492
-1.750 0.1419 0.02600 0.01603 -0.0934 0.8761 0.5645
-1.500 0.1723 0.02594 0.01590 -0.0938 0.8657 0.5781
-1.250 0.2042 0.02586 0.01572 -0.0945 0.8560 0.5910
-1.000 0.2405 0.02572 0.01548 -0.0959 0.8480 0.6042
-0.750 0.2690 0.02570 0.01540 -0.0961 0.8370 0.6168
-0.500 0.3057 0.02551 0.01517 -0.0972 0.8300 0.6300
-0.250 0.3321 0.02550 0.01515 -0.0969 0.8182 0.6420
0.000 0.3612 0.02544 0.01506 -0.0969 0.8072 0.6548
0.250 0.3977 0.02519 0.01477 -0.0980 0.7993 0.6681
0.500 0.4244 0.02519 0.01476 -0.0977 0.7868 0.6811
0.750 0.4517 0.02514 0.01473 -0.0974 0.7754 0.6938
1.000 0.4860 0.02488 0.01448 -0.0979 0.7676 0.7078
1.250 0.5104 0.02492 0.01457 -0.0971 0.7551 0.7221
1.500 0.5364 0.02491 0.01461 -0.0966 0.7434 0.7379
1.750 0.5654 0.02474 0.01449 -0.0962 0.7329 0.7551
2.000 0.5945 0.02453 0.01433 -0.0958 0.7222 0.7740
2.250 0.6177 0.02448 0.01439 -0.0946 0.7093 0.7939
2.500 0.6416 0.02438 0.01439 -0.0935 0.6971 0.8180
2.750 0.6670 0.02415 0.01428 -0.0923 0.6867 0.8502
3.000 0.6956 0.02386 0.01414 -0.0919 0.6757 0.9177
3.250 0.7284 0.02401 0.01429 -0.0931 0.6622 1.0000
3.500 0.7604 0.02421 0.01443 -0.0940 0.6486 1.0000
3.750 0.7916 0.02439 0.01457 -0.0945 0.6350 1.0000
4.000 0.8223 0.02457 0.01474 -0.0949 0.6216 1.0000
4.250 0.8531 0.02475 0.01489 -0.0952 0.6089 1.0000
4.500 0.8836 0.02492 0.01502 -0.0953 0.5956 1.0000
4.750 0.9118 0.02514 0.01526 -0.0951 0.5805 1.0000
5.000 0.9382 0.02543 0.01555 -0.0946 0.5642 1.0000
5.250 0.9637 0.02575 0.01587 -0.0940 0.5473 1.0000
5.500 0.9887 0.02610 0.01626 -0.0934 0.5303 1.0000
5.750 1.0125 0.02649 0.01669 -0.0926 0.5125 1.0000
6.000 1.0359 0.02688 0.01710 -0.0916 0.4939 1.0000
6.250 1.0592 0.02726 0.01751 -0.0907 0.4754 1.0000
6.500 1.0822 0.02766 0.01792 -0.0897 0.4567 1.0000
6.750 1.1022 0.02819 0.01849 -0.0884 0.4364 1.0000
7.000 1.1214 0.02876 0.01911 -0.0871 0.4155 1.0000
7.250 1.1413 0.02933 0.01969 -0.0858 0.3957 1.0000
7.500 1.1604 0.03001 0.02039 -0.0845 0.3765 1.0000
7.750 1.1767 0.03081 0.02124 -0.0829 0.3555 1.0000
8.000 1.1920 0.03161 0.02204 -0.0812 0.3339 1.0000
8.250 1.2047 0.03257 0.02300 -0.0793 0.3115 1.0000
8.500 1.2160 0.03361 0.02400 -0.0773 0.2901 1.0000
8.750 1.2267 0.03475 0.02507 -0.0753 0.2710 1.0000
9.000 1.2352 0.03603 0.02637 -0.0732 0.2528 1.0000
9.250 1.2437 0.03740 0.02776 -0.0712 0.2366 1.0000
9.500 1.2522 0.03888 0.02922 -0.0693 0.2220 1.0000
9.750 1.2597 0.04049 0.03083 -0.0676 0.2080 1.0000
10.000 1.2668 0.04217 0.03250 -0.0659 0.1956 1.0000
10.250 1.2748 0.04396 0.03438 -0.0644 0.1842 1.0000
10.500 1.2834 0.04584 0.03634 -0.0631 0.1740 1.0000
10.750 1.2920 0.04772 0.03821 -0.0618 0.1647 1.0000
11.000 1.2976 0.04985 0.04048 -0.0606 0.1554 1.0000
11.250 1.3032 0.05206 0.04279 -0.0595 0.1472 1.0000
11.500 1.3103 0.05414 0.04490 -0.0585 0.1401 1.0000
11.750 1.3156 0.05663 0.04757 -0.0577 0.1335 1.0000
12.000 1.3220 0.05896 0.04997 -0.0569 0.1274 1.0000
12.250 1.3298 0.06139 0.05250 -0.0562 0.1223 1.0000
12.500 1.3295 0.06463 0.05604 -0.0557 0.1175 1.0000
12.750 1.3346 0.06723 0.05874 -0.0553 0.1129 1.0000
13.000 1.3369 0.07034 0.06200 -0.0550 0.1091 1.0000
13.250 1.3296 0.07467 0.06666 -0.0553 0.1060 1.0000
13.500 1.3250 0.07881 0.07104 -0.0557 0.1033 1.0000
13.750 1.3256 0.08229 0.07465 -0.0559 0.1006 1.0000
14.000 1.3315 0.08522 0.07761 -0.0559 0.0978 1.0000
14.250 1.3075 0.09233 0.08509 -0.0585 0.0966 1.0000
14.500 1.2781 0.10084 0.09393 -0.0623 0.0958 1.0000
14.750 1.2381 0.11216 0.10553 -0.0685 0.0955 1.0000
15.000 1.1697 0.13177 0.12535 -0.0810 0.0961 1.0000
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