WORTMANN FX 60-126 AIRFOIL (fx60126-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 60-126 AIRFOIL (fx60126-il) Reynolds number: 100,000 Max Cl/Cd: 58.51 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx60126-il-100000-n5.txt Download as CSV file: xf-fx60126-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4727 0.07588 0.07058 -0.0577 1.0000 0.0222
-10.500 -0.4942 0.06878 0.06346 -0.0621 1.0000 0.0219
-10.250 -0.5165 0.06266 0.05732 -0.0658 1.0000 0.0217
-10.000 -0.5395 0.05766 0.05228 -0.0684 1.0000 0.0215
-9.750 -0.5653 0.05394 0.04853 -0.0688 1.0000 0.0213
-9.500 -0.5903 0.05112 0.04569 -0.0682 1.0000 0.0211
-9.250 -0.6082 0.04793 0.04237 -0.0689 1.0000 0.0210
-9.000 -0.6199 0.04477 0.03897 -0.0690 1.0000 0.0212
-8.750 -0.6233 0.04173 0.03561 -0.0691 1.0000 0.0215
-8.500 -0.6032 0.03768 0.03095 -0.0733 0.9955 0.0223
-8.250 -0.5752 0.03503 0.02806 -0.0764 0.9905 0.0229
-8.000 -0.5450 0.03277 0.02558 -0.0793 0.9855 0.0236
-7.750 -0.5137 0.03075 0.02333 -0.0817 0.9808 0.0245
-7.500 -0.4837 0.02897 0.02134 -0.0835 0.9754 0.0255
-7.250 -0.4506 0.02730 0.01942 -0.0856 0.9711 0.0270
-7.000 -0.4201 0.02591 0.01795 -0.0873 0.9658 0.0285
-6.750 -0.3875 0.02472 0.01666 -0.0893 0.9602 0.0315
-6.500 -0.3504 0.02348 0.01532 -0.0922 0.9560 0.0368
-6.250 -0.3189 0.02225 0.01401 -0.0939 0.9496 0.0443
-6.000 -0.2834 0.02118 0.01291 -0.0963 0.9443 0.0599
-5.750 -0.2450 0.02003 0.01187 -0.0994 0.9408 0.0864
-5.500 -0.2139 0.01914 0.01112 -0.1010 0.9344 0.1228
-5.250 -0.1785 0.01824 0.01039 -0.1034 0.9291 0.1702
-5.000 -0.1398 0.01757 0.00980 -0.1060 0.9251 0.2181
-4.750 -0.1098 0.01718 0.00948 -0.1067 0.9171 0.2625
-4.500 -0.0740 0.01690 0.00921 -0.1083 0.9116 0.3049
-4.250 -0.0414 0.01676 0.00908 -0.1091 0.9051 0.3392
-4.000 -0.0097 0.01670 0.00896 -0.1097 0.8981 0.3686
-3.750 0.0262 0.01660 0.00877 -0.1110 0.8934 0.3908
-3.500 0.0537 0.01659 0.00869 -0.1108 0.8845 0.4101
-3.250 0.0881 0.01651 0.00853 -0.1117 0.8788 0.4296
-3.000 0.1163 0.01650 0.00845 -0.1115 0.8696 0.4459
-2.750 0.1495 0.01640 0.00828 -0.1121 0.8629 0.4613
-2.500 0.1773 0.01636 0.00819 -0.1118 0.8531 0.4740
-2.250 0.2097 0.01624 0.00802 -0.1122 0.8465 0.4859
-2.000 0.2367 0.01621 0.00795 -0.1118 0.8363 0.4968
-1.750 0.2682 0.01610 0.00775 -0.1122 0.8289 0.5082
-1.500 0.2955 0.01607 0.00771 -0.1117 0.8188 0.5184
-1.250 0.3241 0.01600 0.00762 -0.1115 0.8090 0.5288
-1.000 0.3546 0.01589 0.00742 -0.1116 0.7996 0.5395
-0.750 0.3813 0.01583 0.00737 -0.1111 0.7876 0.5476
-0.500 0.4096 0.01577 0.00726 -0.1109 0.7766 0.5572
-0.250 0.4390 0.01569 0.00715 -0.1108 0.7670 0.5669
0.000 0.4661 0.01568 0.00714 -0.1104 0.7552 0.5765
0.250 0.4941 0.01567 0.00711 -0.1102 0.7436 0.5872
0.500 0.5219 0.01562 0.00706 -0.1098 0.7319 0.5967
0.750 0.5502 0.01557 0.00698 -0.1095 0.7197 0.6064
1.000 0.5780 0.01556 0.00695 -0.1092 0.7064 0.6167
1.250 0.6048 0.01557 0.00697 -0.1087 0.6929 0.6258
1.500 0.6322 0.01560 0.00700 -0.1084 0.6802 0.6364
1.750 0.6597 0.01564 0.00704 -0.1081 0.6679 0.6477
2.000 0.6869 0.01568 0.00708 -0.1077 0.6553 0.6589
2.250 0.7139 0.01573 0.00713 -0.1072 0.6418 0.6711
2.500 0.7407 0.01580 0.00720 -0.1067 0.6278 0.6844
2.750 0.7670 0.01589 0.00732 -0.1062 0.6137 0.6983
3.000 0.7931 0.01600 0.00746 -0.1057 0.6002 0.7128
3.250 0.8188 0.01611 0.00760 -0.1050 0.5855 0.7286
3.500 0.8437 0.01621 0.00775 -0.1042 0.5697 0.7462
3.750 0.8679 0.01631 0.00788 -0.1033 0.5534 0.7666
4.000 0.8912 0.01641 0.00802 -0.1021 0.5369 0.7922
4.250 0.9125 0.01646 0.00819 -0.1006 0.5213 0.8287
4.500 0.9335 0.01638 0.00825 -0.0989 0.5059 1.0000
4.750 0.9604 0.01670 0.00850 -0.0988 0.4889 1.0000
5.000 0.9865 0.01703 0.00877 -0.0986 0.4720 1.0000
5.250 1.0121 0.01739 0.00909 -0.0983 0.4556 1.0000
5.500 1.0371 0.01775 0.00944 -0.0979 0.4384 1.0000
5.750 1.0614 0.01814 0.00982 -0.0973 0.4195 1.0000
6.000 1.0849 0.01856 0.01020 -0.0967 0.3999 1.0000
6.250 1.1078 0.01902 0.01062 -0.0959 0.3799 1.0000
6.500 1.1301 0.01951 0.01107 -0.0951 0.3592 1.0000
6.750 1.1515 0.02005 0.01158 -0.0942 0.3378 1.0000
7.000 1.1722 0.02064 0.01212 -0.0932 0.3167 1.0000
7.250 1.1925 0.02126 0.01271 -0.0922 0.2957 1.0000
7.500 1.2115 0.02196 0.01336 -0.0910 0.2747 1.0000
7.750 1.2294 0.02272 0.01409 -0.0897 0.2523 1.0000
8.000 1.2460 0.02355 0.01485 -0.0883 0.2314 1.0000
8.250 1.2618 0.02444 0.01569 -0.0868 0.2129 1.0000
8.500 1.2770 0.02535 0.01659 -0.0852 0.1964 1.0000
8.750 1.2906 0.02635 0.01756 -0.0835 0.1823 1.0000
9.000 1.3025 0.02736 0.01857 -0.0815 0.1691 1.0000
9.250 1.3136 0.02840 0.01963 -0.0795 0.1564 1.0000
9.500 1.3235 0.02953 0.02077 -0.0774 0.1451 1.0000
9.750 1.3316 0.03079 0.02201 -0.0753 0.1359 1.0000
10.000 1.3396 0.03212 0.02336 -0.0734 0.1275 1.0000
10.250 1.3480 0.03349 0.02481 -0.0715 0.1201 1.0000
10.500 1.3555 0.03496 0.02634 -0.0698 0.1130 1.0000
10.750 1.3632 0.03648 0.02795 -0.0682 0.1070 1.0000
11.000 1.3699 0.03810 0.02965 -0.0667 0.1015 1.0000
11.250 1.3746 0.03995 0.03151 -0.0653 0.0974 1.0000
11.500 1.3819 0.04171 0.03341 -0.0640 0.0928 1.0000
11.750 1.3867 0.04369 0.03549 -0.0629 0.0890 1.0000
12.000 1.3894 0.04595 0.03772 -0.0617 0.0858 1.0000
12.250 1.3967 0.04792 0.03991 -0.0608 0.0820 1.0000
12.500 1.4020 0.05011 0.04224 -0.0600 0.0786 1.0000
12.750 1.4060 0.05245 0.04469 -0.0594 0.0760 1.0000
13.000 1.4093 0.05494 0.04720 -0.0588 0.0739 1.0000
13.250 1.4149 0.05736 0.04983 -0.0582 0.0716 1.0000
13.500 1.4189 0.05997 0.05263 -0.0579 0.0693 1.0000
13.750 1.4217 0.06274 0.05555 -0.0577 0.0673 1.0000
14.000 1.4233 0.06563 0.05857 -0.0577 0.0655 1.0000
14.250 1.4248 0.06859 0.06160 -0.0578 0.0639 1.0000
14.500 1.4266 0.07168 0.06481 -0.0579 0.0623 1.0000
14.750 1.4256 0.07530 0.06867 -0.0583 0.0609 1.0000
15.000 1.4239 0.07910 0.07270 -0.0589 0.0596 1.0000
15.250 1.4212 0.08311 0.07692 -0.0598 0.0584 1.0000
15.500 1.4176 0.08733 0.08133 -0.0609 0.0573 1.0000
15.750 1.4134 0.09173 0.08591 -0.0622 0.0563 1.0000
16.000 1.4090 0.09620 0.09052 -0.0638 0.0553 1.0000
16.250 1.4063 0.10042 0.09485 -0.0653 0.0542 1.0000
16.500 1.4072 0.10408 0.09857 -0.0664 0.0530 1.0000
16.750 1.3957 0.11016 0.10484 -0.0692 0.0522 1.0000
17.000 1.3753 0.11816 0.11315 -0.0738 0.0518 1.0000
17.250 1.3509 0.12743 0.12270 -0.0796 0.0514 1.0000
17.500 1.3196 0.13886 0.13441 -0.0872 0.0513 1.0000
17.750 1.2665 0.15690 0.15272 -0.0999 0.0516 1.0000
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