FX 66-S-161 AIRFOIL (fx66s161-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 66-S-161 AIRFOIL (fx66s161-il) Reynolds number: 200,000 Max Cl/Cd: 73.77 at α=10° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx66s161-il-200000.txt Download as CSV file: xf-fx66s161-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2963 0.11162 0.10847 -0.0482 1.0000 0.0564
-11.000 -0.3195 0.10517 0.10214 -0.0560 1.0000 0.0585
-10.750 -0.3298 0.09944 0.09650 -0.0603 1.0000 0.0587
-10.500 -0.2979 0.09602 0.09309 -0.0585 0.9608 0.0608
-10.250 -0.2506 0.09069 0.08759 -0.0686 0.9128 0.0639
-10.000 -0.1790 0.06974 0.06617 -0.0841 0.7865 0.0734
-9.750 -0.1656 0.06804 0.06436 -0.0827 0.7724 0.0751
-9.500 -0.1670 0.06400 0.06027 -0.0838 0.7626 0.0768
-9.250 -0.1782 0.05823 0.05448 -0.0867 0.7549 0.0784
-9.000 -0.2123 0.04934 0.04558 -0.0932 0.7501 0.0792
-8.750 -0.3900 0.04165 0.03620 -0.1043 0.7702 0.0374
-8.500 -0.3771 0.03766 0.03205 -0.1039 0.7602 0.0352
-8.250 -0.3696 0.03424 0.02825 -0.1028 0.7498 0.0341
-8.000 -0.3575 0.03122 0.02478 -0.1017 0.7411 0.0334
-7.750 -0.3411 0.02876 0.02190 -0.1007 0.7326 0.0333
-7.500 -0.3215 0.02688 0.01968 -0.0999 0.7242 0.0341
-7.250 -0.2996 0.02562 0.01808 -0.0991 0.7168 0.0356
-7.000 -0.2769 0.02450 0.01664 -0.0984 0.7092 0.0372
-6.750 -0.2546 0.02230 0.01433 -0.0978 0.7028 0.0389
-6.500 -0.2310 0.02124 0.01321 -0.0973 0.6967 0.0411
-6.250 -0.2071 0.02039 0.01226 -0.0967 0.6903 0.0444
-6.000 -0.1837 0.01945 0.01119 -0.0961 0.6854 0.0486
-5.750 -0.1610 0.01864 0.01041 -0.0955 0.6797 0.0539
-5.500 -0.1375 0.01792 0.00961 -0.0950 0.6745 0.0603
-5.250 -0.1139 0.01723 0.00887 -0.0946 0.6702 0.0694
-5.000 -0.0907 0.01650 0.00816 -0.0941 0.6650 0.0844
-4.750 -0.0690 0.01535 0.00728 -0.0938 0.6602 0.1347
-4.500 -0.0509 0.01382 0.00679 -0.0934 0.6564 0.3717
-4.250 -0.0244 0.01396 0.00699 -0.0931 0.6524 0.4382
-4.000 0.0026 0.01420 0.00715 -0.0928 0.6479 0.4703
-3.750 0.0298 0.01446 0.00734 -0.0924 0.6439 0.4945
-3.500 0.0575 0.01471 0.00743 -0.0922 0.6405 0.5138
-3.250 0.0844 0.01491 0.00759 -0.0919 0.6365 0.5292
-3.000 0.1112 0.01511 0.00775 -0.0916 0.6324 0.5450
-2.750 0.1383 0.01528 0.00787 -0.0913 0.6288 0.5597
-2.500 0.1657 0.01544 0.00798 -0.0910 0.6258 0.5729
-2.250 0.1928 0.01557 0.00810 -0.0907 0.6227 0.5835
-2.000 0.2199 0.01563 0.00812 -0.0907 0.6191 0.5930
-1.750 0.2473 0.01567 0.00812 -0.0907 0.6158 0.5998
-1.500 0.2758 0.01569 0.00802 -0.0909 0.6128 0.6070
-1.250 0.3041 0.01573 0.00798 -0.0911 0.6102 0.6124
-1.000 0.3315 0.01581 0.00803 -0.0912 0.6070 0.6191
-0.750 0.3586 0.01586 0.00809 -0.0912 0.6038 0.6247
-0.500 0.3862 0.01593 0.00814 -0.0913 0.6008 0.6312
-0.250 0.4145 0.01600 0.00814 -0.0916 0.5982 0.6378
0.000 0.4427 0.01606 0.00817 -0.0917 0.5958 0.6436
0.250 0.4704 0.01621 0.00827 -0.0919 0.5931 0.6503
0.500 0.4966 0.01631 0.00845 -0.0919 0.5896 0.6559
0.750 0.5238 0.01642 0.00857 -0.0919 0.5865 0.6626
1.000 0.5518 0.01648 0.00860 -0.0921 0.5835 0.6695
1.250 0.5802 0.01653 0.00862 -0.0922 0.5808 0.6771
1.500 0.6067 0.01669 0.00882 -0.0922 0.5774 0.6853
1.750 0.6323 0.01684 0.00906 -0.0920 0.5738 0.6941
2.000 0.6590 0.01695 0.00922 -0.0920 0.5706 0.7027
2.250 0.6869 0.01706 0.00933 -0.0922 0.5680 0.7126
2.500 0.7147 0.01716 0.00946 -0.0923 0.5658 0.7217
2.750 0.7410 0.01738 0.00975 -0.0922 0.5633 0.7325
3.000 0.7648 0.01760 0.01013 -0.0918 0.5595 0.7453
3.250 0.7901 0.01774 0.01038 -0.0915 0.5562 0.7605
3.500 0.8165 0.01779 0.01052 -0.0913 0.5533 0.7784
3.750 0.8434 0.01783 0.01063 -0.0911 0.5510 0.8013
4.000 0.8666 0.01799 0.01097 -0.0903 0.5484 0.8328
4.250 0.8875 0.01812 0.01142 -0.0891 0.5445 0.8986
4.500 0.9273 0.01831 0.01167 -0.0921 0.5409 1.0000
4.750 0.9570 0.01850 0.01183 -0.0928 0.5380 1.0000
5.000 0.9874 0.01868 0.01194 -0.0935 0.5356 1.0000
5.250 1.0099 0.01920 0.01256 -0.0931 0.5316 1.0000
5.500 1.0338 0.01958 0.01302 -0.0928 0.5275 1.0000
5.750 1.0612 0.01979 0.01325 -0.0929 0.5242 1.0000
6.000 1.0909 0.01994 0.01337 -0.0934 0.5216 1.0000
6.250 1.1152 0.02037 0.01388 -0.0931 0.5181 1.0000
6.500 1.1358 0.02089 0.01455 -0.0924 0.5134 1.0000
6.750 1.1618 0.02117 0.01489 -0.0923 0.5100 1.0000
7.000 1.1910 0.02134 0.01507 -0.0927 0.5073 1.0000
7.250 1.2184 0.02165 0.01542 -0.0928 0.5043 1.0000
7.500 1.2342 0.02236 0.01635 -0.0914 0.4988 1.0000
7.750 1.2594 0.02264 0.01672 -0.0912 0.4950 1.0000
8.000 1.2900 0.02268 0.01678 -0.0917 0.4921 1.0000
8.250 1.3115 0.02311 0.01735 -0.0909 0.4874 1.0000
8.500 1.3319 0.02335 0.01774 -0.0899 0.4814 1.0000
8.750 1.3689 0.02218 0.01648 -0.0906 0.4740 1.0000
9.000 1.3936 0.02067 0.01493 -0.0892 0.4591 1.0000
9.250 1.4126 0.01984 0.01412 -0.0872 0.4448 1.0000
9.500 1.4296 0.01961 0.01399 -0.0853 0.4331 1.0000
9.750 1.4428 0.01967 0.01421 -0.0830 0.4208 1.0000
10.000 1.4555 0.01973 0.01436 -0.0805 0.4064 1.0000
10.250 1.4639 0.01988 0.01454 -0.0773 0.3886 1.0000
10.500 1.4633 0.02037 0.01505 -0.0729 0.3674 1.0000
10.750 1.4564 0.02128 0.01588 -0.0681 0.3397 1.0000
11.000 1.4410 0.02292 0.01736 -0.0631 0.3083 1.0000
11.250 1.4197 0.02545 0.01973 -0.0587 0.2719 1.0000
11.500 1.3931 0.02900 0.02308 -0.0553 0.2353 1.0000
11.750 1.3665 0.03320 0.02710 -0.0529 0.2031 1.0000
12.000 1.3386 0.03792 0.03165 -0.0511 0.1715 1.0000
12.250 1.3127 0.04274 0.03631 -0.0498 0.1428 1.0000
12.500 1.2861 0.04786 0.04125 -0.0489 0.1132 1.0000
12.750 1.2606 0.05315 0.04634 -0.0483 0.0849 1.0000
13.000 1.2385 0.05839 0.05141 -0.0480 0.0638 1.0000
13.250 1.2214 0.06334 0.05626 -0.0480 0.0515 1.0000
13.500 1.2110 0.06766 0.06059 -0.0481 0.0439 1.0000
13.750 1.2025 0.07191 0.06489 -0.0483 0.0393 1.0000
14.000 1.1978 0.07575 0.06878 -0.0487 0.0354 1.0000
14.250 1.1902 0.07999 0.07306 -0.0491 0.0333 1.0000
14.500 1.1885 0.08354 0.07669 -0.0494 0.0308 1.0000
14.750 1.1891 0.08680 0.08004 -0.0498 0.0285 1.0000
15.000 1.1891 0.09012 0.08339 -0.0502 0.0269 1.0000
15.250 1.1894 0.09298 0.08620 -0.0499 0.0252 1.0000
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