FX 66-S-161 AIRFOIL (fx66s161-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 66-S-161 AIRFOIL (fx66s161-il) Reynolds number: 50,000 Max Cl/Cd: 16.16 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx66s161-il-50000-n5.txt Download as CSV file: xf-fx66s161-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 66-S-161 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3317 0.10179 0.09542 -0.0578 1.0000 0.0471
-10.750 -0.3368 0.09658 0.09031 -0.0600 1.0000 0.0470
-10.500 -0.3449 0.09121 0.08503 -0.0625 1.0000 0.0469
-10.250 -0.3545 0.08625 0.08018 -0.0647 1.0000 0.0467
-10.000 -0.3696 0.08134 0.07540 -0.0669 1.0000 0.0465
-9.750 -0.3896 0.07740 0.07163 -0.0681 1.0000 0.0462
-9.500 -0.3969 0.06980 0.06391 -0.0779 0.9579 0.0460
-9.250 -0.4019 0.06326 0.05709 -0.0871 0.9265 0.0458
-9.000 -0.4036 0.05778 0.05117 -0.0931 0.9017 0.0461
-8.750 -0.4009 0.05313 0.04591 -0.0969 0.8826 0.0469
-8.500 -0.3883 0.04939 0.04180 -0.0988 0.8666 0.0478
-8.250 -0.3725 0.04635 0.03844 -0.0998 0.8518 0.0489
-8.000 -0.3561 0.04373 0.03546 -0.1001 0.8378 0.0501
-7.750 -0.3385 0.04161 0.03302 -0.1000 0.8250 0.0527
-7.500 -0.3200 0.03953 0.03049 -0.0998 0.8134 0.0560
-7.250 -0.2984 0.03752 0.02795 -0.0993 0.8034 0.0588
-7.000 -0.2753 0.03577 0.02612 -0.0988 0.7936 0.0619
-6.750 -0.2535 0.03454 0.02469 -0.0981 0.7841 0.0673
-6.500 -0.2291 0.03322 0.02312 -0.0972 0.7764 0.0731
-6.250 -0.2094 0.03218 0.02205 -0.0961 0.7673 0.0790
-6.000 -0.1883 0.03113 0.02084 -0.0952 0.7604 0.0882
-5.750 -0.1706 0.03024 0.01981 -0.0940 0.7519 0.0986
-5.500 -0.1519 0.02909 0.01869 -0.0933 0.7459 0.1150
-5.250 -0.1365 0.02797 0.01770 -0.0925 0.7383 0.1412
-5.000 -0.1208 0.02626 0.01653 -0.0922 0.7325 0.2090
-4.750 -0.1062 0.02568 0.01691 -0.0904 0.7262 0.3687
-4.500 -0.0849 0.02628 0.01743 -0.0887 0.7198 0.4476
-4.250 -0.0609 0.02692 0.01781 -0.0872 0.7152 0.4972
-4.000 -0.0421 0.02766 0.01848 -0.0850 0.7084 0.5316
-3.750 -0.0201 0.02820 0.01887 -0.0830 0.7034 0.5610
-3.500 0.0036 0.02853 0.01904 -0.0813 0.6994 0.5814
-3.250 0.0235 0.02879 0.01917 -0.0800 0.6933 0.5971
-3.000 0.0476 0.02881 0.01899 -0.0793 0.6886 0.6108
-2.750 0.0746 0.02870 0.01862 -0.0793 0.6849 0.6229
-2.500 0.0948 0.02888 0.01868 -0.0786 0.6790 0.6322
-2.250 0.1192 0.02889 0.01852 -0.0784 0.6744 0.6410
-2.000 0.1465 0.02882 0.01821 -0.0787 0.6708 0.6507
-1.750 0.1675 0.02903 0.01833 -0.0780 0.6658 0.6582
-1.500 0.1905 0.02920 0.01835 -0.0779 0.6609 0.6675
-1.250 0.2162 0.02925 0.01827 -0.0777 0.6571 0.6753
-1.000 0.2421 0.02935 0.01820 -0.0778 0.6536 0.6845
-0.750 0.2599 0.02982 0.01865 -0.0770 0.6479 0.6934
-0.500 0.2836 0.03003 0.01877 -0.0767 0.6439 0.7026
0.000 0.3284 0.03066 0.01927 -0.0759 0.6360 0.7224
0.250 0.3472 0.03116 0.01976 -0.0753 0.6311 0.7324
0.500 0.3723 0.03140 0.01992 -0.0752 0.6276 0.7435
0.750 0.3995 0.03149 0.01995 -0.0751 0.6249 0.7546
1.000 0.4078 0.03257 0.02112 -0.0735 0.6187 0.7659
1.250 0.4274 0.03308 0.02164 -0.0729 0.6144 0.7790
1.500 0.4528 0.03326 0.02182 -0.0726 0.6114 0.7941
1.750 0.4679 0.03398 0.02260 -0.0714 0.6068 0.8110
2.000 0.4774 0.03500 0.02372 -0.0699 0.6008 0.8312
2.250 0.5026 0.03525 0.02404 -0.0697 0.5974 0.8571
2.500 0.5399 0.03522 0.02406 -0.0712 0.5949 0.8941
2.750 0.5523 0.03716 0.02612 -0.0725 0.5863 1.0000
3.000 0.5798 0.03775 0.02660 -0.0736 0.5826 1.0000
3.250 0.6137 0.03798 0.02671 -0.0749 0.5801 1.0000
3.750 0.6288 0.04134 0.03001 -0.0733 0.5672 1.0000
4.000 0.6608 0.04164 0.03023 -0.0740 0.5650 1.0000
4.500 0.6645 0.04569 0.03428 -0.0712 0.5515 1.0000
5.000 0.6694 0.05006 0.03864 -0.0692 0.5381 1.0000
5.250 0.6979 0.05054 0.03910 -0.0694 0.5356 1.0000
5.500 0.6801 0.05422 0.04280 -0.0678 0.5255 1.0000
5.750 0.7048 0.05496 0.04355 -0.0678 0.5222 1.0000
6.250 0.7144 0.05930 0.04795 -0.0665 0.5092 1.0000
6.500 0.7410 0.05992 0.04861 -0.0665 0.5064 1.0000
6.750 0.7290 0.06339 0.05212 -0.0655 0.4973 1.0000
7.000 0.7488 0.06452 0.05331 -0.0653 0.4932 1.0000
7.250 0.7766 0.06509 0.05395 -0.0653 0.4906 1.0000
7.500 0.7595 0.06908 0.05798 -0.0645 0.4810 1.0000
7.750 0.7824 0.07000 0.05898 -0.0644 0.4774 1.0000
8.250 0.7923 0.07471 0.06382 -0.0637 0.4647 1.0000
8.500 0.8177 0.07548 0.06471 -0.0636 0.4617 1.0000
8.750 0.8070 0.07908 0.06838 -0.0632 0.4524 1.0000
9.000 0.8285 0.08013 0.06954 -0.0631 0.4484 1.0000
9.250 0.8267 0.08311 0.07260 -0.0629 0.4407 1.0000
9.500 0.8414 0.08469 0.07430 -0.0627 0.4352 1.0000
9.750 0.8683 0.08524 0.07501 -0.0625 0.4322 1.0000
10.000 0.8568 0.08910 0.07895 -0.0624 0.4220 1.0000
10.250 0.8817 0.08978 0.07979 -0.0622 0.4184 1.0000
10.500 0.8741 0.09337 0.08347 -0.0622 0.4087 1.0000
10.750 0.8989 0.09393 0.08419 -0.0619 0.4045 1.0000
11.000 0.8937 0.09733 0.08770 -0.0620 0.3947 1.0000
11.250 0.9193 0.09769 0.08827 -0.0615 0.3903 1.0000
11.500 0.9138 0.10119 0.09188 -0.0618 0.3800 1.0000
11.750 0.9412 0.10123 0.09213 -0.0612 0.3757 1.0000
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