WORTMANN FX M2 AIRFOIL (fxm2-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX M2 AIRFOIL (fxm2-il) Reynolds number: 100,000 Max Cl/Cd: 50.68 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fxm2-il-100000-n5.txt Download as CSV file: xf-fxm2-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX M2 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
------ -------- --------- --------- -------- -------- --------
-7.250 -0.2686 0.09474 0.09009 -0.0155 1.0000 0.0343
-7.000 -0.2693 0.09269 0.08812 -0.0147 1.0000 0.0348
-6.750 -0.2723 0.09073 0.08625 -0.0138 1.0000 0.0353
-6.500 -0.2732 0.08857 0.08418 -0.0135 1.0000 0.0358
-6.250 -0.2720 0.08624 0.08193 -0.0140 1.0000 0.0363
-6.000 -0.2697 0.08384 0.07960 -0.0153 1.0000 0.0370
-5.750 -0.2647 0.08128 0.07710 -0.0184 1.0000 0.0376
-5.500 -0.2550 0.07840 0.07424 -0.0228 1.0000 0.0379
-5.250 -0.2274 0.07381 0.06963 -0.0300 0.9954 0.0384
-5.000 -0.2060 0.07010 0.06598 -0.0300 0.9883 0.0400
-4.750 -0.1461 0.06490 0.06053 -0.0471 0.9770 0.0451
-4.500 -0.1177 0.06022 0.05588 -0.0508 0.9676 0.0460
-4.250 -0.0932 0.05680 0.05248 -0.0528 0.9562 0.0478
-4.000 -0.0561 0.05301 0.04859 -0.0587 0.9453 0.0511
-3.750 -0.0073 0.04840 0.04369 -0.0676 0.9338 0.0550
-3.500 0.0184 0.04541 0.04072 -0.0691 0.9197 0.0577
-3.250 0.0650 0.04180 0.03677 -0.0755 0.9051 0.0655
-3.000 0.1040 0.03892 0.03372 -0.0796 0.8870 0.0767
-2.750 0.1439 0.03611 0.03069 -0.0834 0.8634 0.0884
-2.250 0.2454 0.02843 0.02196 -0.0914 0.7953 0.0516
-2.000 0.2897 0.02614 0.01908 -0.0941 0.7451 0.0514
-1.750 0.3261 0.02439 0.01677 -0.0952 0.6943 0.0505
-1.500 0.3588 0.02296 0.01471 -0.0955 0.6491 0.0485
-1.250 0.3891 0.02187 0.01306 -0.0953 0.6077 0.0477
-1.000 0.4175 0.02110 0.01192 -0.0950 0.5717 0.0492
-0.750 0.4455 0.02053 0.01092 -0.0945 0.5414 0.0515
-0.500 0.4734 0.01985 0.00996 -0.0940 0.5134 0.0518
-0.250 0.5005 0.01933 0.00913 -0.0934 0.4855 0.0522
0.000 0.5273 0.01894 0.00847 -0.0927 0.4629 0.0532
0.250 0.5540 0.01848 0.00795 -0.0922 0.4379 0.0561
0.500 0.5798 0.01823 0.00754 -0.0916 0.4178 0.0582
0.750 0.6056 0.01805 0.00721 -0.0909 0.4006 0.0596
1.000 0.6318 0.01788 0.00698 -0.0903 0.3809 0.0614
1.250 0.6580 0.01785 0.00680 -0.0897 0.3627 0.0653
1.500 0.6839 0.01791 0.00667 -0.0892 0.3487 0.0698
1.750 0.7104 0.01804 0.00661 -0.0887 0.3354 0.0736
2.000 0.7376 0.01813 0.00660 -0.0884 0.3217 0.0796
2.250 0.7647 0.01819 0.00664 -0.0880 0.3096 0.0962
2.500 0.7810 0.01651 0.00678 -0.0855 0.3015 1.0000
2.750 0.8071 0.01689 0.00686 -0.0850 0.2936 1.0000
3.000 0.8333 0.01729 0.00705 -0.0845 0.2861 1.0000
3.250 0.8590 0.01776 0.00731 -0.0840 0.2797 1.0000
3.500 0.8855 0.01814 0.00763 -0.0836 0.2722 1.0000
3.750 0.9116 0.01856 0.00794 -0.0832 0.2657 1.0000
4.000 0.9379 0.01892 0.00827 -0.0828 0.2582 1.0000
4.250 0.9639 0.01929 0.00858 -0.0824 0.2518 1.0000
4.500 0.9895 0.01966 0.00888 -0.0820 0.2460 1.0000
4.750 1.0149 0.02007 0.00921 -0.0815 0.2405 1.0000
5.000 1.0399 0.02052 0.00954 -0.0810 0.2354 1.0000
5.250 1.0649 0.02103 0.00996 -0.0806 0.2305 1.0000
5.500 1.0899 0.02155 0.01048 -0.0801 0.2255 1.0000
5.750 1.1148 0.02217 0.01097 -0.0797 0.2219 1.0000
6.000 1.1400 0.02268 0.01159 -0.0792 0.2172 1.0000
6.250 1.1646 0.02323 0.01217 -0.0787 0.2126 1.0000
6.500 1.1890 0.02378 0.01274 -0.0782 0.2081 1.0000
6.750 1.2133 0.02424 0.01338 -0.0777 0.2024 1.0000
7.000 1.2370 0.02472 0.01387 -0.0771 0.1978 1.0000
7.250 1.2609 0.02519 0.01448 -0.0765 0.1925 1.0000
7.500 1.2842 0.02563 0.01496 -0.0759 0.1879 1.0000
7.750 1.3070 0.02612 0.01550 -0.0752 0.1836 1.0000
8.000 1.3296 0.02668 0.01616 -0.0745 0.1787 1.0000
8.250 1.3515 0.02722 0.01673 -0.0738 0.1744 1.0000
8.500 1.3727 0.02786 0.01730 -0.0730 0.1707 1.0000
8.750 1.3943 0.02860 0.01829 -0.0722 0.1660 1.0000
9.000 1.4151 0.02935 0.01916 -0.0714 0.1617 1.0000
9.250 1.4352 0.03010 0.01998 -0.0705 0.1582 1.0000
9.500 1.4546 0.03093 0.02080 -0.0695 0.1552 1.0000
9.750 1.4740 0.03185 0.02201 -0.0686 0.1511 1.0000
10.000 1.4922 0.03278 0.02311 -0.0675 0.1472 1.0000
10.250 1.5096 0.03366 0.02411 -0.0664 0.1439 1.0000
10.500 1.5261 0.03453 0.02505 -0.0652 0.1412 1.0000
10.750 1.5416 0.03562 0.02630 -0.0639 0.1384 1.0000
11.000 1.5560 0.03683 0.02774 -0.0626 0.1355 1.0000
11.250 1.5690 0.03804 0.02913 -0.0611 0.1329 1.0000
11.500 1.5807 0.03924 0.03048 -0.0595 0.1308 1.0000
11.750 1.5899 0.04043 0.03181 -0.0577 0.1290 1.0000
12.000 1.5976 0.04166 0.03313 -0.0557 0.1275 1.0000
12.250 1.6045 0.04300 0.03452 -0.0538 0.1262 1.0000
12.500 1.6063 0.04496 0.03674 -0.0518 0.1247 1.0000
12.750 1.6059 0.04713 0.03916 -0.0499 0.1233 1.0000
13.000 1.6032 0.04958 0.04183 -0.0484 0.1219 1.0000
13.250 1.5983 0.05235 0.04482 -0.0472 0.1206 1.0000
13.500 1.5911 0.05551 0.04820 -0.0466 0.1193 1.0000
13.750 1.5816 0.05915 0.05204 -0.0466 0.1181 1.0000
14.000 1.5701 0.06336 0.05643 -0.0474 0.1170 1.0000
14.250 1.5563 0.06822 0.06147 -0.0489 0.1159 1.0000
14.500 1.5402 0.07382 0.06723 -0.0511 0.1149 1.0000
14.750 1.5216 0.08023 0.07381 -0.0542 0.1140 1.0000
15.000 1.5029 0.08701 0.08073 -0.0575 0.1130 1.0000
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