FX 66-S-161 AIRFOIL (fx66s161-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 66-S-161 AIRFOIL (fx66s161-il) Reynolds number: 500,000 Max Cl/Cd: 114.91 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx66s161-il-500000-n5.txt Download as CSV file: xf-fx66s161-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.5650 0.09136 0.08884 -0.0498 1.0000 0.0070
-14.000 -0.6164 0.07617 0.07345 -0.0586 1.0000 0.0069
-13.750 -0.6416 0.06761 0.06476 -0.0640 1.0000 0.0068
-13.500 -0.6659 0.05992 0.05689 -0.0690 1.0000 0.0069
-13.250 -0.6799 0.05414 0.05096 -0.0730 0.9990 0.0069
-13.000 -0.6535 0.04483 0.04121 -0.0913 0.9214 0.0070
-12.500 -0.6278 0.03615 0.03154 -0.1054 0.7894 0.0071
-12.250 -0.6362 0.03327 0.02840 -0.1057 0.7602 0.0073
-12.000 -0.6386 0.03097 0.02587 -0.1056 0.7399 0.0072
-11.750 -0.6384 0.02905 0.02377 -0.1053 0.7224 0.0073
-11.500 -0.6365 0.02746 0.02202 -0.1047 0.7078 0.0074
-11.250 -0.6379 0.02593 0.02034 -0.1031 0.6959 0.0075
-10.750 -0.6218 0.02409 0.01823 -0.1000 0.6753 0.0078
-10.500 -0.6077 0.02326 0.01728 -0.0990 0.6665 0.0080
-10.250 -0.5918 0.02248 0.01637 -0.0981 0.6580 0.0082
-10.000 -0.5742 0.02175 0.01553 -0.0973 0.6506 0.0085
-9.750 -0.5564 0.02095 0.01458 -0.0964 0.6434 0.0088
-9.500 -0.5378 0.02015 0.01363 -0.0957 0.6372 0.0091
-9.250 -0.5182 0.01939 0.01273 -0.0950 0.6307 0.0093
-8.750 -0.4775 0.01790 0.01101 -0.0937 0.6192 0.0099
-8.500 -0.4562 0.01721 0.01024 -0.0931 0.6133 0.0102
-8.250 -0.4334 0.01669 0.00964 -0.0927 0.6077 0.0106
-8.000 -0.4097 0.01620 0.00906 -0.0924 0.6021 0.0111
-7.750 -0.3857 0.01575 0.00852 -0.0920 0.5969 0.0117
-7.500 -0.3613 0.01531 0.00799 -0.0917 0.5925 0.0124
-7.250 -0.3365 0.01489 0.00748 -0.0915 0.5879 0.0129
-7.000 -0.3121 0.01440 0.00694 -0.0912 0.5834 0.0139
-6.750 -0.2866 0.01408 0.00654 -0.0910 0.5795 0.0151
-6.500 -0.2604 0.01379 0.00619 -0.0909 0.5756 0.0166
-6.250 -0.2346 0.01340 0.00576 -0.0908 0.5716 0.0185
-6.000 -0.2085 0.01311 0.00541 -0.0907 0.5678 0.0203
-5.750 -0.1819 0.01288 0.00509 -0.0906 0.5644 0.0221
-5.500 -0.1553 0.01256 0.00475 -0.0906 0.5611 0.0248
-5.250 -0.1283 0.01233 0.00448 -0.0906 0.5574 0.0282
-5.000 -0.1015 0.01207 0.00421 -0.0905 0.5538 0.0339
-4.750 -0.0746 0.01185 0.00396 -0.0905 0.5505 0.0413
-4.500 -0.0474 0.01160 0.00372 -0.0906 0.5476 0.0524
-4.250 -0.0202 0.01134 0.00349 -0.0906 0.5447 0.0709
-4.000 0.0068 0.01103 0.00327 -0.0907 0.5417 0.0999
-3.750 0.0333 0.01065 0.00303 -0.0908 0.5388 0.1466
-3.500 0.0593 0.01017 0.00276 -0.0909 0.5358 0.2199
-3.250 0.0856 0.00971 0.00258 -0.0910 0.5330 0.3083
-3.000 0.1129 0.00945 0.00248 -0.0911 0.5301 0.3634
-2.750 0.1405 0.00932 0.00246 -0.0912 0.5274 0.4051
-2.500 0.1687 0.00929 0.00244 -0.0913 0.5250 0.4302
-2.250 0.1970 0.00931 0.00244 -0.0914 0.5228 0.4527
-2.000 0.2252 0.00935 0.00245 -0.0915 0.5206 0.4697
-1.750 0.2537 0.00938 0.00246 -0.0916 0.5184 0.4826
-1.500 0.2822 0.00938 0.00246 -0.0918 0.5160 0.4907
-1.250 0.3108 0.00941 0.00245 -0.0919 0.5136 0.4965
-1.000 0.3394 0.00944 0.00243 -0.0921 0.5115 0.5006
-0.750 0.3677 0.00945 0.00242 -0.0922 0.5095 0.5042
-0.500 0.3960 0.00949 0.00242 -0.0923 0.5076 0.5080
-0.250 0.4242 0.00955 0.00243 -0.0925 0.5057 0.5120
0.000 0.4528 0.00958 0.00245 -0.0927 0.5039 0.5158
0.250 0.4812 0.00959 0.00248 -0.0928 0.5016 0.5197
0.500 0.5095 0.00961 0.00250 -0.0930 0.4987 0.5238
0.750 0.5377 0.00965 0.00253 -0.0931 0.4959 0.5278
1.000 0.5658 0.00970 0.00256 -0.0932 0.4934 0.5314
1.250 0.5938 0.00976 0.00261 -0.0933 0.4915 0.5351
1.500 0.6219 0.00982 0.00267 -0.0935 0.4895 0.5392
1.750 0.6503 0.00986 0.00273 -0.0936 0.4875 0.5436
2.000 0.6785 0.00990 0.00280 -0.0938 0.4855 0.5478
2.250 0.7065 0.00994 0.00288 -0.0939 0.4833 0.5524
2.500 0.7345 0.01000 0.00295 -0.0941 0.4810 0.5582
2.750 0.7623 0.01005 0.00303 -0.0942 0.4788 0.5643
3.000 0.7899 0.01013 0.00312 -0.0942 0.4766 0.5705
3.250 0.8176 0.01020 0.00322 -0.0943 0.4747 0.5765
3.500 0.8455 0.01024 0.00334 -0.0945 0.4727 0.5831
4.000 0.9008 0.01035 0.00359 -0.0947 0.4682 0.5994
4.250 0.9283 0.01042 0.00370 -0.0947 0.4658 0.6076
4.500 0.9555 0.01050 0.00382 -0.0948 0.4634 0.6164
4.750 0.9824 0.01060 0.00396 -0.0947 0.4610 0.6260
5.000 1.0098 0.01065 0.00411 -0.0948 0.4584 0.6373
5.250 1.0369 0.01071 0.00427 -0.0948 0.4554 0.6498
5.500 1.0636 0.01077 0.00443 -0.0948 0.4523 0.6636
5.750 1.0901 0.01085 0.00459 -0.0947 0.4494 0.6797
6.000 1.1161 0.01094 0.00476 -0.0945 0.4468 0.6988
6.250 1.1424 0.01099 0.00497 -0.0944 0.4441 0.7227
6.500 1.1682 0.01102 0.00518 -0.0942 0.4412 0.7554
6.750 1.1926 0.01102 0.00538 -0.0936 0.4379 0.8032
7.000 1.2158 0.01088 0.00555 -0.0926 0.4346 0.9284
7.250 1.2467 0.01102 0.00575 -0.0936 0.4306 1.0000
7.500 1.2724 0.01114 0.00595 -0.0934 0.4242 1.0000
7.750 1.2962 0.01128 0.00611 -0.0928 0.4134 1.0000
8.000 1.3166 0.01153 0.00628 -0.0917 0.3908 1.0000
8.250 1.3321 0.01206 0.00665 -0.0899 0.3581 1.0000
8.500 1.3425 0.01286 0.00724 -0.0873 0.3196 1.0000
8.750 1.3533 0.01364 0.00788 -0.0848 0.2899 1.0000
9.000 1.3545 0.01470 0.00874 -0.0808 0.2493 1.0000
9.250 1.3474 0.01595 0.00978 -0.0756 0.2102 1.0000
9.500 1.3366 0.01747 0.01111 -0.0703 0.1747 1.0000
9.750 1.3251 0.01923 0.01273 -0.0657 0.1445 1.0000
10.000 1.3094 0.02158 0.01494 -0.0616 0.1138 1.0000
10.250 1.3004 0.02394 0.01724 -0.0589 0.0925 1.0000
10.500 1.2903 0.02671 0.01994 -0.0568 0.0724 1.0000
10.750 1.2822 0.02956 0.02274 -0.0552 0.0551 1.0000
11.250 1.2703 0.03529 0.02843 -0.0529 0.0319 1.0000
11.750 1.2672 0.04047 0.03364 -0.0514 0.0207 1.0000
12.000 1.2674 0.04296 0.03617 -0.0507 0.0179 1.0000
12.250 1.2684 0.04541 0.03868 -0.0502 0.0160 1.0000
12.500 1.2687 0.04803 0.04133 -0.0498 0.0141 1.0000
12.750 1.2712 0.05048 0.04385 -0.0495 0.0131 1.0000
13.000 1.2731 0.05306 0.04649 -0.0493 0.0119 1.0000
13.250 1.2740 0.05581 0.04929 -0.0492 0.0109 1.0000
13.500 1.2763 0.05847 0.05203 -0.0491 0.0102 1.0000
13.750 1.2799 0.06101 0.05464 -0.0491 0.0093 1.0000
14.000 1.2817 0.06382 0.05750 -0.0492 0.0084 1.0000
14.250 1.2839 0.06662 0.06036 -0.0494 0.0082 1.0000
14.500 1.2848 0.06963 0.06343 -0.0496 0.0077 1.0000
14.750 1.2876 0.07247 0.06636 -0.0498 0.0073 1.0000
15.000 1.2902 0.07537 0.06933 -0.0502 0.0069 1.0000
15.250 1.2921 0.07841 0.07244 -0.0506 0.0066 1.0000
15.500 1.2943 0.08142 0.07552 -0.0511 0.0063 1.0000
15.750 1.2947 0.08475 0.07891 -0.0516 0.0059 1.0000
16.000 1.2952 0.08811 0.08234 -0.0523 0.0057 1.0000
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