FX 66-S-161 AIRFOIL (fx66s161-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 66-S-161 AIRFOIL (fx66s161-il) Reynolds number: 100,000 Max Cl/Cd: 42.39 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx66s161-il-100000-n5.txt Download as CSV file: xf-fx66s161-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3306 0.09569 0.09120 -0.0551 1.0000 0.0263
-10.750 -0.3413 0.08913 0.08473 -0.0581 1.0000 0.0261
-10.500 -0.3565 0.07818 0.07382 -0.0658 0.9638 0.0257
-10.250 -0.3931 0.06240 0.05776 -0.0830 0.9136 0.0240
-10.000 -0.4111 0.05302 0.04785 -0.0957 0.8703 0.0236
-9.500 -0.4199 0.04660 0.04075 -0.0999 0.8119 0.0246
-9.250 -0.4207 0.04398 0.03776 -0.0998 0.7937 0.0253
-9.000 -0.4186 0.04127 0.03464 -0.0994 0.7788 0.0259
-8.750 -0.4124 0.03860 0.03152 -0.0987 0.7661 0.0267
-8.500 -0.4014 0.03608 0.02852 -0.0980 0.7550 0.0272
-8.250 -0.3865 0.03378 0.02575 -0.0973 0.7454 0.0279
-8.000 -0.3684 0.03182 0.02336 -0.0966 0.7353 0.0286
-7.750 -0.3483 0.02998 0.02139 -0.0963 0.7268 0.0297
-7.500 -0.3272 0.02885 0.02015 -0.0959 0.7182 0.0316
-7.250 -0.3051 0.02776 0.01884 -0.0955 0.7105 0.0342
-7.000 -0.2820 0.02663 0.01743 -0.0949 0.7033 0.0365
-6.750 -0.2605 0.02536 0.01611 -0.0943 0.6970 0.0387
-6.500 -0.2385 0.02454 0.01525 -0.0938 0.6903 0.0424
-6.250 -0.2154 0.02377 0.01427 -0.0932 0.6850 0.0466
-6.000 -0.1948 0.02284 0.01336 -0.0925 0.6785 0.0506
-5.750 -0.1720 0.02221 0.01259 -0.0920 0.6728 0.0575
-5.500 -0.1501 0.02142 0.01173 -0.0914 0.6677 0.0649
-5.250 -0.1276 0.02071 0.01100 -0.0910 0.6619 0.0776
-5.000 -0.1044 0.01997 0.01024 -0.0908 0.6572 0.0999
-4.750 -0.0823 0.01898 0.00949 -0.0907 0.6530 0.1564
-4.500 -0.0627 0.01779 0.00904 -0.0905 0.6482 0.3080
-4.250 -0.0386 0.01768 0.00922 -0.0898 0.6440 0.4017
-4.000 -0.0118 0.01785 0.00926 -0.0895 0.6403 0.4470
-3.750 0.0144 0.01808 0.00938 -0.0891 0.6358 0.4785
-3.500 0.0405 0.01830 0.00949 -0.0886 0.6313 0.5040
-3.250 0.0667 0.01852 0.00959 -0.0880 0.6275 0.5253
-3.000 0.0936 0.01868 0.00959 -0.0876 0.6244 0.5431
-2.750 0.1195 0.01879 0.00965 -0.0872 0.6202 0.5551
-2.500 0.1464 0.01881 0.00956 -0.0871 0.6162 0.5643
-2.250 0.1738 0.01880 0.00941 -0.0871 0.6128 0.5717
-2.000 0.2019 0.01879 0.00922 -0.0872 0.6099 0.5782
-1.750 0.2284 0.01883 0.00921 -0.0871 0.6059 0.5841
-1.500 0.2555 0.01887 0.00915 -0.0872 0.6021 0.5914
-1.250 0.2825 0.01890 0.00911 -0.0871 0.5988 0.5971
-1.000 0.3105 0.01893 0.00901 -0.0873 0.5960 0.6039
-0.750 0.3376 0.01899 0.00902 -0.0873 0.5931 0.6096
-0.500 0.3637 0.01911 0.00913 -0.0872 0.5895 0.6161
-0.250 0.3906 0.01920 0.00918 -0.0873 0.5862 0.6231
0.000 0.4177 0.01927 0.00921 -0.0872 0.5832 0.6298
0.250 0.4458 0.01934 0.00920 -0.0874 0.5807 0.6378
0.500 0.4719 0.01948 0.00935 -0.0872 0.5777 0.6451
0.750 0.4973 0.01968 0.00959 -0.0871 0.5743 0.6532
1.000 0.5231 0.01983 0.00977 -0.0869 0.5713 0.6608
1.250 0.5500 0.01996 0.00988 -0.0869 0.5684 0.6689
1.500 0.5773 0.02005 0.00995 -0.0869 0.5660 0.6772
1.750 0.6038 0.02022 0.01014 -0.0869 0.5632 0.6860
2.000 0.6277 0.02050 0.01052 -0.0866 0.5594 0.6962
2.250 0.6529 0.02068 0.01076 -0.0863 0.5559 0.7066
2.500 0.6795 0.02078 0.01091 -0.0862 0.5528 0.7184
2.750 0.7071 0.02085 0.01098 -0.0861 0.5503 0.7316
3.000 0.7299 0.02113 0.01140 -0.0856 0.5465 0.7459
3.250 0.7526 0.02139 0.01180 -0.0850 0.5426 0.7626
3.500 0.7770 0.02154 0.01207 -0.0844 0.5394 0.7841
3.750 0.8021 0.02160 0.01224 -0.0839 0.5369 0.8121
4.000 0.8287 0.02161 0.01236 -0.0835 0.5349 0.8544
4.250 0.8590 0.02203 0.01307 -0.0848 0.5305 1.0000
4.500 0.8832 0.02248 0.01355 -0.0848 0.5268 1.0000
4.750 0.9101 0.02277 0.01383 -0.0850 0.5237 1.0000
5.000 0.9386 0.02299 0.01404 -0.0854 0.5213 1.0000
5.250 0.9614 0.02352 0.01463 -0.0851 0.5180 1.0000
5.500 0.9799 0.02425 0.01548 -0.0843 0.5136 1.0000
5.750 1.0038 0.02467 0.01596 -0.0840 0.5102 1.0000
6.000 1.0312 0.02491 0.01624 -0.0841 0.5074 1.0000
6.250 1.0607 0.02507 0.01641 -0.0845 0.5053 1.0000
6.500 1.0696 0.02623 0.01779 -0.0825 0.4993 1.0000
6.750 1.0910 0.02675 0.01841 -0.0819 0.4954 1.0000
7.000 1.1180 0.02698 0.01870 -0.0819 0.4925 1.0000
7.250 1.1483 0.02709 0.01885 -0.0823 0.4903 1.0000
7.500 1.1481 0.02864 0.02065 -0.0793 0.4834 1.0000
7.750 1.1691 0.02915 0.02127 -0.0787 0.4797 1.0000
8.000 1.1971 0.02934 0.02156 -0.0788 0.4771 1.0000
8.250 1.2045 0.03051 0.02291 -0.0766 0.4719 1.0000
8.500 1.2106 0.03167 0.02423 -0.0743 0.4664 1.0000
8.750 1.2370 0.03185 0.02452 -0.0742 0.4633 1.0000
9.000 1.2724 0.03159 0.02439 -0.0750 0.4610 1.0000
9.250 1.2320 0.03468 0.02766 -0.0677 0.4514 1.0000
9.500 1.2655 0.03434 0.02745 -0.0681 0.4484 1.0000
9.750 1.2096 0.03904 0.03224 -0.0614 0.4375 1.0000
10.000 1.2437 0.03833 0.03168 -0.0613 0.4345 1.0000
10.250 1.2816 0.03729 0.03079 -0.0615 0.4308 1.0000
10.750 1.1907 0.04885 0.04245 -0.0559 0.4057 1.0000
11.250 1.2080 0.05080 0.04461 -0.0540 0.3859 1.0000
11.500 1.2146 0.05152 0.04539 -0.0529 0.3685 1.0000
11.750 1.2286 0.05133 0.04520 -0.0518 0.3437 1.0000
12.000 1.2270 0.05365 0.04753 -0.0511 0.3229 1.0000
12.250 1.2339 0.05501 0.04886 -0.0503 0.3015 1.0000
12.500 1.2269 0.05830 0.05217 -0.0499 0.2792 1.0000
12.750 1.2274 0.06035 0.05401 -0.0490 0.2417 1.0000
13.000 1.2181 0.06376 0.05710 -0.0485 0.2018 1.0000
13.250 1.2033 0.06822 0.06133 -0.0485 0.1691 1.0000
13.500 1.1862 0.07329 0.06617 -0.0488 0.1393 1.0000
13.750 1.1701 0.07849 0.07119 -0.0494 0.1119 1.0000
14.000 1.1562 0.08360 0.07613 -0.0502 0.0884 1.0000
14.250 1.1448 0.08853 0.08094 -0.0510 0.0705 1.0000
14.500 1.1361 0.09321 0.08555 -0.0519 0.0573 1.0000
14.750 1.1293 0.09772 0.09002 -0.0528 0.0483 1.0000
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