FX 66-S-161 AIRFOIL (fx66s161-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 66-S-161 AIRFOIL (fx66s161-il) Reynolds number: 200,000 Max Cl/Cd: 75.66 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx66s161-il-200000-n5.txt Download as CSV file: xf-fx66s161-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4528 0.05344 0.04935 -0.0929 0.8731 0.0137
-11.000 -0.4647 0.04655 0.04194 -0.1010 0.8270 0.0136
-10.750 -0.4746 0.04238 0.03740 -0.1041 0.7959 0.0137
-10.500 -0.4833 0.03951 0.03422 -0.1047 0.7725 0.0138
-10.250 -0.4926 0.03722 0.03164 -0.1034 0.7541 0.0138
-10.000 -0.4940 0.03523 0.02936 -0.1021 0.7393 0.0140
-9.750 -0.4893 0.03337 0.02721 -0.1010 0.7266 0.0143
-9.250 -0.4692 0.02984 0.02309 -0.0989 0.7049 0.0149
-9.000 -0.4550 0.02821 0.02117 -0.0980 0.6959 0.0154
-8.750 -0.4385 0.02671 0.01938 -0.0971 0.6874 0.0160
-8.500 -0.4202 0.02537 0.01778 -0.0962 0.6797 0.0165
-8.250 -0.4007 0.02424 0.01641 -0.0955 0.6723 0.0172
-8.000 -0.3810 0.02327 0.01538 -0.0949 0.6655 0.0181
-7.750 -0.3596 0.02258 0.01459 -0.0945 0.6588 0.0193
-7.500 -0.3380 0.02177 0.01362 -0.0939 0.6530 0.0205
-7.250 -0.3162 0.02089 0.01260 -0.0932 0.6469 0.0216
-7.000 -0.2952 0.02000 0.01158 -0.0925 0.6414 0.0228
-6.750 -0.2731 0.01928 0.01079 -0.0921 0.6360 0.0243
-6.500 -0.2497 0.01871 0.01014 -0.0917 0.6303 0.0265
-6.250 -0.2261 0.01817 0.00946 -0.0913 0.6257 0.0293
-6.000 -0.2025 0.01757 0.00882 -0.0911 0.6210 0.0323
-5.750 -0.1775 0.01715 0.00829 -0.0908 0.6163 0.0363
-5.500 -0.1533 0.01658 0.00765 -0.0906 0.6122 0.0413
-5.250 -0.1279 0.01618 0.00714 -0.0904 0.6086 0.0476
-5.000 -0.1024 0.01572 0.00666 -0.0903 0.6043 0.0582
-4.750 -0.0770 0.01524 0.00621 -0.0902 0.6004 0.0760
-4.250 -0.0274 0.01405 0.00535 -0.0902 0.5935 0.1864
-4.000 -0.0037 0.01327 0.00507 -0.0902 0.5895 0.3105
-3.750 0.0221 0.01301 0.00504 -0.0901 0.5859 0.3856
-3.500 0.0493 0.01302 0.00505 -0.0900 0.5828 0.4281
-3.250 0.0772 0.01308 0.00501 -0.0899 0.5801 0.4532
-3.000 0.1049 0.01316 0.00505 -0.0899 0.5768 0.4746
-2.750 0.1326 0.01324 0.00508 -0.0898 0.5733 0.4938
-2.500 0.1602 0.01332 0.00510 -0.0897 0.5700 0.5103
-2.250 0.1880 0.01337 0.00508 -0.0897 0.5671 0.5212
-2.000 0.2162 0.01343 0.00498 -0.0898 0.5646 0.5292
-1.750 0.2442 0.01341 0.00495 -0.0898 0.5614 0.5339
-1.500 0.2722 0.01342 0.00492 -0.0899 0.5583 0.5388
-1.250 0.3005 0.01346 0.00486 -0.0901 0.5557 0.5443
-1.000 0.3285 0.01347 0.00484 -0.0902 0.5531 0.5490
-0.750 0.3567 0.01351 0.00481 -0.0903 0.5508 0.5543
-0.500 0.3849 0.01357 0.00479 -0.0905 0.5483 0.5600
-0.250 0.4126 0.01359 0.00483 -0.0905 0.5453 0.5642
0.000 0.4405 0.01364 0.00487 -0.0906 0.5427 0.5691
0.250 0.4686 0.01370 0.00489 -0.0908 0.5403 0.5745
0.500 0.4964 0.01374 0.00493 -0.0909 0.5381 0.5791
0.750 0.5244 0.01381 0.00498 -0.0910 0.5361 0.5846
1.000 0.5524 0.01390 0.00504 -0.0911 0.5338 0.5912
1.250 0.5796 0.01396 0.00517 -0.0911 0.5309 0.5974
1.500 0.6071 0.01404 0.00527 -0.0912 0.5280 0.6047
1.750 0.6345 0.01410 0.00536 -0.0912 0.5251 0.6111
2.000 0.6621 0.01416 0.00541 -0.0912 0.5223 0.6181
2.250 0.6899 0.01424 0.00548 -0.0913 0.5199 0.6246
2.500 0.7166 0.01433 0.00566 -0.0913 0.5168 0.6321
2.750 0.7435 0.01442 0.00583 -0.0913 0.5140 0.6404
3.000 0.7705 0.01452 0.00599 -0.0913 0.5115 0.6503
3.250 0.7975 0.01461 0.00615 -0.0912 0.5092 0.6601
3.500 0.8248 0.01471 0.00629 -0.0913 0.5071 0.6705
4.000 0.8778 0.01494 0.00671 -0.0911 0.5018 0.6959
4.250 0.9034 0.01504 0.00695 -0.0908 0.4988 0.7122
4.500 0.9290 0.01513 0.00717 -0.0905 0.4961 0.7314
4.750 0.9546 0.01521 0.00738 -0.0902 0.4937 0.7557
5.000 0.9804 0.01528 0.00756 -0.0898 0.4915 0.7883
5.250 1.0044 0.01532 0.00779 -0.0891 0.4890 0.8386
5.500 1.0373 0.01533 0.00809 -0.0903 0.4854 1.0000
5.750 1.0632 0.01554 0.00836 -0.0902 0.4820 1.0000
6.000 1.0897 0.01574 0.00859 -0.0902 0.4791 1.0000
6.250 1.1168 0.01592 0.00878 -0.0903 0.4765 1.0000
6.500 1.1418 0.01618 0.00913 -0.0900 0.4732 1.0000
6.750 1.1660 0.01644 0.00951 -0.0897 0.4694 1.0000
7.000 1.1911 0.01666 0.00981 -0.0895 0.4659 1.0000
7.250 1.2171 0.01687 0.01008 -0.0894 0.4631 1.0000
7.500 1.2433 0.01710 0.01037 -0.0893 0.4604 1.0000
7.750 1.2652 0.01743 0.01088 -0.0886 0.4561 1.0000
8.000 1.2888 0.01770 0.01126 -0.0881 0.4522 1.0000
8.250 1.3136 0.01791 0.01156 -0.0878 0.4488 1.0000
8.500 1.3359 0.01812 0.01190 -0.0871 0.4433 1.0000
8.750 1.3558 0.01812 0.01196 -0.0858 0.4332 1.0000
9.000 1.3694 0.01810 0.01201 -0.0835 0.4143 1.0000
9.250 1.3793 0.01823 0.01207 -0.0805 0.3886 1.0000
9.500 1.3855 0.01870 0.01246 -0.0773 0.3619 1.0000
9.750 1.3881 0.01936 0.01306 -0.0735 0.3383 1.0000
10.000 1.3855 0.02033 0.01395 -0.0693 0.3156 1.0000
10.250 1.3799 0.02165 0.01518 -0.0653 0.2902 1.0000
10.500 1.3679 0.02355 0.01697 -0.0613 0.2609 1.0000
10.750 1.3519 0.02612 0.01941 -0.0580 0.2310 1.0000
11.000 1.3323 0.02943 0.02259 -0.0553 0.2019 1.0000
11.250 1.3134 0.03311 0.02615 -0.0533 0.1753 1.0000
11.500 1.2940 0.03711 0.03004 -0.0518 0.1500 1.0000
11.750 1.2775 0.04103 0.03387 -0.0507 0.1263 1.0000
12.000 1.2605 0.04515 0.03788 -0.0498 0.1033 1.0000
12.250 1.2463 0.04911 0.04176 -0.0491 0.0831 1.0000
12.500 1.2341 0.05306 0.04562 -0.0487 0.0650 1.0000
12.750 1.2241 0.05693 0.04943 -0.0484 0.0501 1.0000
13.000 1.2176 0.06057 0.05304 -0.0484 0.0398 1.0000
13.500 1.2109 0.06741 0.05991 -0.0485 0.0276 1.0000
13.750 1.2084 0.07085 0.06340 -0.0488 0.0244 1.0000
14.000 1.2085 0.07404 0.06667 -0.0490 0.0216 1.0000
14.250 1.2074 0.07746 0.07016 -0.0494 0.0200 1.0000
14.500 1.2058 0.08099 0.07376 -0.0499 0.0185 1.0000
14.750 1.2064 0.08430 0.07718 -0.0504 0.0170 1.0000
15.000 1.2070 0.08764 0.08060 -0.0510 0.0158 1.0000
15.250 1.2055 0.09133 0.08436 -0.0517 0.0149 1.0000
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