FX 66-182 AIRFOIL (fx66182-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 66-182 AIRFOIL (fx66182-il) Reynolds number: 50,000 Max Cl/Cd: 8.19 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx66182-il-50000-n5.txt Download as CSV file: xf-fx66182-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 66-182 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.3118 0.11475 0.10846 -0.0617 1.0000 0.0514
-12.000 -0.3124 0.11070 0.10452 -0.0629 1.0000 0.0511
-11.750 -0.3177 0.10598 0.09994 -0.0646 1.0000 0.0509
-11.500 -0.3241 0.10040 0.09450 -0.0674 0.9957 0.0507
-11.250 -0.3263 0.09159 0.08568 -0.0754 0.9483 0.0504
-11.000 -0.3343 0.08281 0.07678 -0.0843 0.9216 0.0500
-10.750 -0.3465 0.07451 0.06826 -0.0933 0.9003 0.0496
-10.500 -0.3589 0.06776 0.06124 -0.1006 0.8794 0.0494
-10.250 -0.3713 0.06264 0.05577 -0.1051 0.8589 0.0494
-10.000 -0.3849 0.05883 0.05160 -0.1068 0.8409 0.0497
-9.750 -0.3974 0.05594 0.04833 -0.1063 0.8261 0.0502
-9.500 -0.4038 0.05317 0.04513 -0.1055 0.8137 0.0508
-9.250 -0.4060 0.05047 0.04187 -0.1044 0.8034 0.0516
-9.000 -0.3969 0.04800 0.03918 -0.1036 0.7931 0.0525
-8.750 -0.3830 0.04589 0.03686 -0.1031 0.7846 0.0541
-8.500 -0.3684 0.04416 0.03491 -0.1024 0.7762 0.0565
-8.250 -0.3526 0.04233 0.03274 -0.1016 0.7689 0.0593
-8.000 -0.3328 0.04049 0.03050 -0.1008 0.7616 0.0614
-7.750 -0.3058 0.03873 0.02845 -0.1005 0.7558 0.0639
-7.500 -0.2826 0.03759 0.02729 -0.1000 0.7487 0.0680
-7.250 -0.2538 0.03651 0.02596 -0.0995 0.7431 0.0728
-7.000 -0.2255 0.03556 0.02486 -0.0987 0.7376 0.0768
-6.750 -0.2064 0.03477 0.02408 -0.0974 0.7317 0.0814
-6.500 -0.1876 0.03405 0.02314 -0.0961 0.7270 0.0891
-6.250 -0.1762 0.03325 0.02244 -0.0944 0.7218 0.0973
-6.000 -0.1658 0.03244 0.02168 -0.0926 0.7163 0.1085
-5.750 -0.1558 0.03140 0.02073 -0.0909 0.7118 0.1272
-5.500 -0.1495 0.03018 0.01979 -0.0892 0.7075 0.1666
-5.250 -0.1491 0.02882 0.01914 -0.0869 0.7023 0.2568
-5.000 -0.1392 0.02939 0.02103 -0.0817 0.6982 0.4523
-4.750 -0.1210 0.03049 0.02190 -0.0792 0.6946 0.5373
-4.500 -0.1063 0.03181 0.02305 -0.0759 0.6900 0.5809
-4.250 -0.0882 0.03308 0.02418 -0.0724 0.6853 0.6096
-4.000 -0.0668 0.03386 0.02476 -0.0697 0.6815 0.6317
-3.750 -0.0430 0.03430 0.02496 -0.0677 0.6785 0.6497
-3.500 -0.0285 0.03469 0.02523 -0.0655 0.6742 0.6641
-3.250 -0.0144 0.03493 0.02530 -0.0636 0.6698 0.6772
-3.000 0.0052 0.03501 0.02520 -0.0623 0.6662 0.6879
-2.750 0.0287 0.03496 0.02495 -0.0615 0.6633 0.6966
-2.500 0.0417 0.03506 0.02489 -0.0603 0.6592 0.7064
-2.250 0.0549 0.03540 0.02516 -0.0584 0.6546 0.7127
-2.000 0.0723 0.03545 0.02503 -0.0577 0.6511 0.7209
-1.750 0.0957 0.03544 0.02487 -0.0573 0.6483 0.7264
-1.500 0.1175 0.03548 0.02473 -0.0569 0.6454 0.7328
-1.250 0.1191 0.03621 0.02545 -0.0546 0.6395 0.7391
-1.000 0.1363 0.03649 0.02564 -0.0536 0.6358 0.7445
-0.750 0.1599 0.03659 0.02558 -0.0537 0.6330 0.7507
-0.500 0.1868 0.03660 0.02543 -0.0540 0.6309 0.7559
-0.250 0.1794 0.03790 0.02679 -0.0507 0.6242 0.7614
0.000 0.1946 0.03842 0.02721 -0.0501 0.6201 0.7674
0.250 0.2176 0.03868 0.02737 -0.0500 0.6174 0.7719
0.500 0.2449 0.03881 0.02738 -0.0503 0.6154 0.7769
0.750 0.2302 0.04073 0.02934 -0.0472 0.6079 0.7830
1.000 0.2457 0.04139 0.02996 -0.0464 0.6040 0.7877
1.250 0.2696 0.04175 0.03024 -0.0465 0.6014 0.7928
1.500 0.2985 0.04200 0.03038 -0.0473 0.5995 0.7983
1.750 0.2677 0.04481 0.03330 -0.0429 0.5906 0.8041
2.000 0.2882 0.04545 0.03389 -0.0428 0.5872 0.8097
2.250 0.3158 0.04584 0.03420 -0.0435 0.5850 0.8156
2.750 0.3182 0.04938 0.03778 -0.0412 0.5742 0.8283
3.000 0.3403 0.05005 0.03844 -0.0413 0.5711 0.8347
3.250 0.3673 0.05050 0.03887 -0.0418 0.5689 0.8418
3.500 0.3610 0.05279 0.04122 -0.0405 0.5626 0.8503
3.750 0.3734 0.05405 0.04252 -0.0402 0.5581 0.8592
4.000 0.3968 0.05477 0.04328 -0.0405 0.5551 0.8689
4.250 0.4243 0.05539 0.04393 -0.0412 0.5530 0.8807
4.500 0.4213 0.05786 0.04652 -0.0410 0.5467 0.8979
4.750 0.4431 0.05926 0.04803 -0.0426 0.5422 0.9242
5.000 0.4701 0.06013 0.04891 -0.0442 0.5391 1.0000
5.250 0.4999 0.06101 0.04975 -0.0457 0.5371 1.0000
5.500 0.4901 0.06404 0.05278 -0.0454 0.5303 1.0000
5.750 0.5080 0.06550 0.05424 -0.0462 0.5262 1.0000
6.000 0.5341 0.06655 0.05527 -0.0472 0.5233 1.0000
6.250 0.5539 0.06801 0.05671 -0.0479 0.5203 1.0000
6.500 0.5489 0.07074 0.05947 -0.0476 0.5136 1.0000
6.750 0.5690 0.07209 0.06083 -0.0482 0.5099 1.0000
7.000 0.5955 0.07311 0.06186 -0.0489 0.5072 1.0000
7.500 0.6071 0.07737 0.06617 -0.0488 0.4959 1.0000
7.750 0.6315 0.07849 0.06733 -0.0493 0.4928 1.0000
8.000 0.6346 0.08080 0.06969 -0.0492 0.4868 1.0000
8.250 0.6455 0.08265 0.07159 -0.0493 0.4814 1.0000
8.500 0.6688 0.08383 0.07281 -0.0496 0.4780 1.0000
8.750 0.6722 0.08616 0.07522 -0.0495 0.4718 1.0000
9.000 0.6839 0.08796 0.07709 -0.0496 0.4662 1.0000
9.250 0.7086 0.08902 0.07822 -0.0499 0.4628 1.0000
9.500 0.7065 0.09169 0.08097 -0.0498 0.4550 1.0000
9.750 0.7246 0.09309 0.08245 -0.0499 0.4500 1.0000
10.000 0.7525 0.09387 0.08335 -0.0502 0.4470 1.0000
10.250 0.7442 0.09698 0.08654 -0.0500 0.4374 1.0000
10.500 0.7690 0.09789 0.08756 -0.0501 0.4335 1.0000
10.750 0.7665 0.10072 0.09048 -0.0502 0.4248 1.0000
11.000 0.7881 0.10177 0.09168 -0.0502 0.4198 1.0000
11.250 0.7904 0.10428 0.09429 -0.0503 0.4117 1.0000
11.500 0.8094 0.10542 0.09557 -0.0503 0.4058 1.0000
12.000 0.8321 0.10891 0.09931 -0.0504 0.3914 1.0000
12.250 0.8361 0.11127 0.10182 -0.0506 0.3827 1.0000
12.500 0.8563 0.11212 0.10283 -0.0505 0.3765 1.0000
12.750 0.8579 0.11472 0.10556 -0.0507 0.3667 1.0000
13.000 0.8826 0.11493 0.10594 -0.0504 0.3610 1.0000
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