FX 66-S-171 AIRFOIL (fx66s171-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 66-S-171 AIRFOIL (fx66s171-il) Reynolds number: 200,000 Max Cl/Cd: 72.42 at α=9.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx66s171-il-200000-n5.txt Download as CSV file: xf-fx66s171-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 66-S-171 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.4437 0.08604 0.08258 -0.0595 1.0000 0.0143
-12.500 -0.4916 0.07240 0.06876 -0.0684 1.0000 0.0140
-12.250 -0.5186 0.06207 0.05818 -0.0778 0.9425 0.0138
-12.000 -0.5176 0.05165 0.04718 -0.0942 0.8842 0.0139
-11.750 -0.5169 0.04563 0.04062 -0.1023 0.8334 0.0140
-11.500 -0.5209 0.04174 0.03629 -0.1052 0.7999 0.0141
-11.250 -0.5255 0.03869 0.03289 -0.1062 0.7752 0.0143
-11.000 -0.5288 0.03620 0.03006 -0.1061 0.7561 0.0145
-10.750 -0.5290 0.03414 0.02771 -0.1053 0.7404 0.0147
-10.500 -0.5288 0.03230 0.02556 -0.1039 0.7270 0.0150
-10.250 -0.5247 0.03088 0.02388 -0.1020 0.7155 0.0152
-10.000 -0.5154 0.02949 0.02237 -0.1008 0.7055 0.0156
-9.750 -0.5033 0.02848 0.02123 -0.0998 0.6962 0.0161
-9.500 -0.4889 0.02754 0.02017 -0.0988 0.6875 0.0167
-9.250 -0.4732 0.02663 0.01909 -0.0979 0.6798 0.0175
-9.000 -0.4562 0.02564 0.01791 -0.0970 0.6722 0.0184
-8.750 -0.4384 0.02465 0.01671 -0.0961 0.6653 0.0193
-8.500 -0.4215 0.02356 0.01553 -0.0951 0.6587 0.0200
-8.250 -0.4033 0.02271 0.01460 -0.0943 0.6522 0.0208
-8.000 -0.3840 0.02196 0.01375 -0.0935 0.6464 0.0219
-7.750 -0.3639 0.02120 0.01290 -0.0928 0.6404 0.0232
-7.500 -0.3431 0.02054 0.01207 -0.0921 0.6352 0.0248
-7.250 -0.3225 0.01985 0.01134 -0.0916 0.6304 0.0271
-7.000 -0.3000 0.01930 0.01071 -0.0912 0.6253 0.0296
-6.750 -0.2781 0.01867 0.00997 -0.0906 0.6208 0.0324
-6.500 -0.2550 0.01817 0.00940 -0.0903 0.6169 0.0361
-6.250 -0.2313 0.01765 0.00879 -0.0900 0.6124 0.0403
-6.000 -0.2075 0.01713 0.00823 -0.0897 0.6082 0.0462
-5.750 -0.1834 0.01665 0.00769 -0.0894 0.6044 0.0541
-5.500 -0.1587 0.01620 0.00720 -0.0892 0.6009 0.0663
-5.250 -0.1340 0.01571 0.00675 -0.0891 0.5967 0.0868
-5.000 -0.1096 0.01516 0.00631 -0.0890 0.5928 0.1232
-4.750 -0.0860 0.01447 0.00585 -0.0889 0.5895 0.1903
-4.500 -0.0632 0.01371 0.00550 -0.0888 0.5868 0.3011
-4.250 -0.0375 0.01343 0.00543 -0.0887 0.5834 0.3683
-4.000 -0.0107 0.01339 0.00547 -0.0885 0.5801 0.4087
-3.750 0.0170 0.01344 0.00545 -0.0885 0.5770 0.4340
-3.500 0.0448 0.01351 0.00543 -0.0884 0.5741 0.4537
-3.250 0.0727 0.01363 0.00542 -0.0884 0.5715 0.4713
-3.000 0.1004 0.01371 0.00547 -0.0884 0.5682 0.4870
-2.750 0.1282 0.01379 0.00550 -0.0883 0.5650 0.4996
-2.500 0.1560 0.01384 0.00547 -0.0883 0.5620 0.5094
-2.250 0.1840 0.01386 0.00542 -0.0884 0.5593 0.5161
-2.000 0.2125 0.01390 0.00530 -0.0885 0.5570 0.5218
-1.750 0.2405 0.01390 0.00528 -0.0886 0.5546 0.5256
-1.500 0.2685 0.01391 0.00527 -0.0887 0.5518 0.5300
-1.250 0.2966 0.01394 0.00523 -0.0889 0.5490 0.5348
-1.000 0.3247 0.01396 0.00519 -0.0890 0.5463 0.5391
-0.750 0.3527 0.01399 0.00518 -0.0891 0.5440 0.5433
-0.500 0.3810 0.01404 0.00516 -0.0892 0.5420 0.5483
-0.250 0.4092 0.01411 0.00518 -0.0894 0.5399 0.5533
0.000 0.4368 0.01415 0.00525 -0.0895 0.5375 0.5571
0.250 0.4646 0.01421 0.00531 -0.0896 0.5350 0.5615
0.500 0.4925 0.01427 0.00535 -0.0898 0.5326 0.5663
0.750 0.5204 0.01432 0.00538 -0.0899 0.5302 0.5704
1.000 0.5483 0.01438 0.00543 -0.0900 0.5281 0.5751
1.250 0.5766 0.01448 0.00548 -0.0902 0.5263 0.5812
1.500 0.6035 0.01456 0.00564 -0.0902 0.5236 0.5868
1.750 0.6305 0.01463 0.00576 -0.0901 0.5204 0.5925
2.000 0.6579 0.01470 0.00583 -0.0902 0.5173 0.5985
2.250 0.6852 0.01476 0.00592 -0.0902 0.5146 0.6036
2.500 0.7130 0.01485 0.00601 -0.0903 0.5125 0.6095
2.750 0.7409 0.01498 0.00613 -0.0905 0.5107 0.6156
3.000 0.7671 0.01509 0.00637 -0.0904 0.5081 0.6220
3.500 0.8203 0.01532 0.00675 -0.0903 0.5028 0.6375
3.750 0.8473 0.01542 0.00691 -0.0903 0.5003 0.6460
4.000 0.8743 0.01552 0.00706 -0.0903 0.4981 0.6545
4.250 0.9019 0.01564 0.00721 -0.0904 0.4962 0.6637
4.500 0.9273 0.01580 0.00751 -0.0902 0.4936 0.6742
4.750 0.9526 0.01595 0.00780 -0.0899 0.4908 0.6860
5.000 0.9780 0.01609 0.00807 -0.0897 0.4881 0.7001
5.250 1.0034 0.01619 0.00829 -0.0894 0.4855 0.7175
5.750 1.0554 0.01636 0.00867 -0.0889 0.4809 0.7667
6.000 1.0772 0.01648 0.00905 -0.0879 0.4777 0.8057
6.250 1.1006 0.01649 0.00936 -0.0871 0.4744 0.8847
6.500 1.1335 0.01663 0.00961 -0.0885 0.4712 1.0000
6.750 1.1598 0.01681 0.00982 -0.0885 0.4684 1.0000
7.000 1.1872 0.01700 0.01001 -0.0886 0.4660 1.0000
7.250 1.2089 0.01733 0.01050 -0.0879 0.4621 1.0000
7.500 1.2324 0.01762 0.01089 -0.0875 0.4587 1.0000
7.750 1.2568 0.01786 0.01121 -0.0872 0.4557 1.0000
8.000 1.2824 0.01806 0.01147 -0.0870 0.4528 1.0000
8.250 1.3061 0.01834 0.01184 -0.0866 0.4496 1.0000
8.500 1.3264 0.01872 0.01238 -0.0857 0.4457 1.0000
8.750 1.3486 0.01902 0.01279 -0.0851 0.4419 1.0000
9.000 1.3726 0.01916 0.01299 -0.0846 0.4379 1.0000
9.250 1.3878 0.01938 0.01336 -0.0827 0.4293 1.0000
9.500 1.4003 0.01936 0.01340 -0.0802 0.4150 1.0000
9.750 1.4071 0.01943 0.01343 -0.0768 0.3956 1.0000
10.000 1.4077 0.01984 0.01379 -0.0726 0.3753 1.0000
10.250 1.4081 0.02056 0.01447 -0.0688 0.3553 1.0000
10.500 1.4062 0.02157 0.01542 -0.0652 0.3363 1.0000
10.750 1.4025 0.02290 0.01673 -0.0619 0.3185 1.0000
11.000 1.3964 0.02463 0.01842 -0.0590 0.2995 1.0000
11.250 1.3852 0.02697 0.02070 -0.0562 0.2759 1.0000
11.500 1.3694 0.02998 0.02362 -0.0538 0.2516 1.0000
11.750 1.3513 0.03351 0.02706 -0.0519 0.2258 1.0000
12.000 1.3311 0.03747 0.03092 -0.0503 0.2025 1.0000
12.250 1.3116 0.04158 0.03494 -0.0490 0.1805 1.0000
12.500 1.2918 0.04590 0.03916 -0.0480 0.1576 1.0000
12.750 1.2735 0.05028 0.04344 -0.0473 0.1360 1.0000
13.000 1.2586 0.05452 0.04761 -0.0469 0.1156 1.0000
13.250 1.2440 0.05891 0.05189 -0.0468 0.0949 1.0000
13.500 1.2310 0.06327 0.05615 -0.0468 0.0757 1.0000
13.750 1.2221 0.06729 0.06011 -0.0469 0.0600 1.0000
14.000 1.2145 0.07127 0.06403 -0.0471 0.0471 1.0000
14.250 1.2100 0.07497 0.06773 -0.0475 0.0389 1.0000
14.500 1.2066 0.07861 0.07137 -0.0478 0.0326 1.0000
14.750 1.2034 0.08229 0.07506 -0.0483 0.0278 1.0000
15.000 1.2031 0.08568 0.07853 -0.0488 0.0249 1.0000
15.250 1.2016 0.08926 0.08216 -0.0494 0.0224 1.0000
15.500 1.2004 0.09287 0.08584 -0.0501 0.0206 1.0000
15.750 1.2011 0.09625 0.08932 -0.0508 0.0192 1.0000
16.000 1.2002 0.09991 0.09305 -0.0517 0.0178 1.0000
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