WORTMANN FX 60-126/1 AIRFOIL (fx601261-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 60-126/1 AIRFOIL (fx601261-il) Reynolds number: 50,000 Max Cl/Cd: 34.45 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx601261-il-50000.txt Download as CSV file: xf-fx601261-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 60-126/1 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2823 0.10562 0.09919 -0.0295 1.0000 0.2444
-8.000 -0.3073 0.10552 0.09932 -0.0291 1.0000 0.2499
-7.750 -0.2989 0.10176 0.09562 -0.0280 1.0000 0.2513
-7.500 -0.2999 0.09912 0.09310 -0.0266 1.0000 0.2524
-7.250 -0.3087 0.09715 0.09126 -0.0247 1.0000 0.2527
-7.000 -0.3705 0.09055 0.08488 -0.0289 1.0000 0.1559
-6.750 -0.4157 0.08509 0.07961 -0.0323 1.0000 0.1295
-6.500 -0.4376 0.07816 0.07275 -0.0376 1.0000 0.1154
-6.250 -0.4570 0.06847 0.06296 -0.0476 1.0000 0.1047
-6.000 -0.4544 0.06372 0.05811 -0.0498 1.0000 0.0994
-5.750 -0.4424 0.05206 0.04526 -0.0644 1.0000 0.0886
-5.500 -0.4248 0.04811 0.04115 -0.0658 1.0000 0.0868
-5.250 -0.4013 0.04400 0.03663 -0.0684 1.0000 0.0849
-5.000 -0.3739 0.04030 0.03239 -0.0709 1.0000 0.0833
-4.750 -0.3459 0.03734 0.02892 -0.0725 1.0000 0.0828
-4.500 -0.3196 0.03514 0.02631 -0.0732 1.0000 0.0834
-4.250 -0.2945 0.03340 0.02426 -0.0731 1.0000 0.0853
-4.000 -0.2706 0.03215 0.02267 -0.0727 1.0000 0.0886
-3.750 -0.2490 0.03095 0.02160 -0.0722 1.0000 0.0950
-3.500 -0.2256 0.03002 0.02056 -0.0719 1.0000 0.1045
-3.250 -0.2006 0.02892 0.01959 -0.0722 1.0000 0.1211
-3.000 -0.1603 0.02674 0.01921 -0.0757 1.0000 0.3753
-2.750 -0.1537 0.02891 0.02154 -0.0711 1.0000 0.4613
-2.500 -0.1498 0.03063 0.02341 -0.0657 1.0000 0.5070
-2.250 -0.1526 0.03222 0.02525 -0.0583 1.0000 0.5459
-2.000 -0.1449 0.03300 0.02600 -0.0542 1.0000 0.5834
-1.750 -0.1336 0.03316 0.02610 -0.0514 1.0000 0.6060
-1.500 -0.1004 0.03354 0.02627 -0.0529 0.9920 0.6349
-1.250 -0.0621 0.03389 0.02638 -0.0555 0.9814 0.6626
-1.000 -0.0240 0.03425 0.02653 -0.0582 0.9705 0.6902
-0.750 0.0094 0.03449 0.02662 -0.0598 0.9595 0.7130
-0.500 0.0443 0.03471 0.02665 -0.0622 0.9478 0.7358
-0.250 0.0751 0.03493 0.02675 -0.0635 0.9358 0.7576
0.000 0.1095 0.03523 0.02690 -0.0657 0.9239 0.7805
0.250 0.1420 0.03550 0.02707 -0.0672 0.9123 0.8025
0.500 0.1792 0.03582 0.02729 -0.0696 0.9009 0.8268
0.750 0.2012 0.03601 0.02747 -0.0695 0.8887 0.8507
1.000 0.2242 0.03623 0.02768 -0.0695 0.8766 0.8795
1.250 0.2527 0.03642 0.02794 -0.0705 0.8647 0.9218
1.500 0.3026 0.03699 0.02843 -0.0768 0.8501 1.0000
1.750 0.3577 0.03793 0.02920 -0.0841 0.8363 1.0000
2.000 0.4113 0.03885 0.02994 -0.0906 0.8227 1.0000
2.250 0.4648 0.03968 0.03063 -0.0965 0.8099 1.0000
2.500 0.4999 0.04072 0.03155 -0.0996 0.7960 1.0000
2.750 0.5324 0.04178 0.03251 -0.1019 0.7823 1.0000
3.000 0.5629 0.04286 0.03351 -0.1037 0.7687 1.0000
3.250 0.5944 0.04383 0.03441 -0.1052 0.7546 1.0000
3.500 0.6254 0.04475 0.03529 -0.1063 0.7404 1.0000
3.750 0.6555 0.04565 0.03616 -0.1072 0.7264 1.0000
4.000 0.6848 0.04657 0.03707 -0.1078 0.7126 1.0000
4.250 0.7146 0.04745 0.03799 -0.1084 0.6993 1.0000
4.500 0.7473 0.04814 0.03869 -0.1090 0.6862 1.0000
4.750 0.7856 0.04835 0.03894 -0.1098 0.6729 1.0000
5.000 0.8182 0.04862 0.03930 -0.1097 0.6579 1.0000
5.250 0.8646 0.04791 0.03869 -0.1103 0.6446 1.0000
5.500 0.8941 0.04823 0.03908 -0.1098 0.6299 1.0000
5.750 0.9298 0.04798 0.03895 -0.1094 0.6152 1.0000
6.000 0.9753 0.04665 0.03774 -0.1091 0.6001 1.0000
6.250 1.0251 0.04470 0.03594 -0.1087 0.5848 1.0000
6.500 1.0446 0.04517 0.03651 -0.1068 0.5662 1.0000
6.750 1.0796 0.04426 0.03572 -0.1056 0.5479 1.0000
7.000 1.1369 0.04136 0.03293 -0.1053 0.5287 1.0000
7.250 1.1898 0.03898 0.03058 -0.1051 0.5078 1.0000
7.500 1.2121 0.03922 0.03093 -0.1032 0.4853 1.0000
7.750 1.2499 0.03833 0.03002 -0.1023 0.4613 1.0000
8.000 1.2865 0.03745 0.02900 -0.1013 0.4343 1.0000
8.250 1.3034 0.03802 0.02964 -0.0990 0.4078 1.0000
8.500 1.3227 0.03856 0.03013 -0.0969 0.3813 1.0000
8.750 1.3446 0.03903 0.03048 -0.0951 0.3557 1.0000
9.000 1.3652 0.04005 0.03142 -0.0936 0.3328 1.0000
9.250 1.3847 0.04152 0.03286 -0.0921 0.3130 1.0000
9.500 1.3985 0.04339 0.03487 -0.0903 0.2954 1.0000
9.750 1.4132 0.04515 0.03668 -0.0885 0.2786 1.0000
10.000 1.4273 0.04669 0.03824 -0.0867 0.2619 1.0000
10.250 1.4411 0.04818 0.03972 -0.0848 0.2460 1.0000
10.500 1.4508 0.05014 0.04177 -0.0828 0.2327 1.0000
10.750 1.4594 0.05228 0.04401 -0.0808 0.2207 1.0000
11.000 1.4746 0.05463 0.04644 -0.0796 0.2100 1.0000
11.250 1.4749 0.05760 0.04970 -0.0771 0.2023 1.0000
11.500 1.4789 0.06084 0.05312 -0.0752 0.1956 1.0000
11.750 1.4568 0.06474 0.05740 -0.0713 0.1924 1.0000
12.000 1.4861 0.06754 0.06015 -0.0716 0.1836 1.0000
12.250 1.4517 0.07198 0.06494 -0.0675 0.1829 1.0000
12.500 1.4131 0.07743 0.07069 -0.0650 0.1828 1.0000
12.750 1.3697 0.08437 0.07786 -0.0643 0.1832 1.0000
13.000 1.3218 0.09322 0.08689 -0.0659 0.1841 1.0000
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