FX 63-143 AIRFOIL (fx63143-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 63-143 AIRFOIL (fx63143-il) Reynolds number: 50,000 Max Cl/Cd: 23.98 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63143-il-50000-n5.txt Download as CSV file: xf-fx63143-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 63-143 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3677 0.10202 0.09526 -0.0432 1.0000 0.0397
-10.000 -0.3780 0.09547 0.08880 -0.0472 1.0000 0.0372
-9.750 -0.3792 0.09131 0.08473 -0.0488 1.0000 0.0367
-9.500 -0.3837 0.08648 0.07998 -0.0512 1.0000 0.0361
-9.250 -0.3938 0.08126 0.07483 -0.0541 1.0000 0.0355
-9.000 -0.4102 0.07662 0.07025 -0.0558 1.0000 0.0346
-8.750 -0.4455 0.07196 0.06556 -0.0554 1.0000 0.0332
-8.500 -0.4634 0.06940 0.06305 -0.0530 1.0000 0.0331
-8.250 -0.4767 0.06694 0.06062 -0.0505 1.0000 0.0328
-8.000 -0.4936 0.06467 0.05836 -0.0473 1.0000 0.0327
-7.750 -0.5114 0.06317 0.05689 -0.0432 1.0000 0.0324
-7.500 -0.4989 0.05834 0.05170 -0.0464 0.9801 0.0323
-7.250 -0.4841 0.05387 0.04680 -0.0485 0.9583 0.0322
-7.000 -0.4646 0.04972 0.04216 -0.0503 0.9409 0.0321
-6.750 -0.4412 0.04590 0.03781 -0.0518 0.9261 0.0321
-6.500 -0.4126 0.04222 0.03354 -0.0534 0.9138 0.0323
-6.250 -0.3804 0.03889 0.02958 -0.0549 0.9022 0.0329
-6.000 -0.3482 0.03629 0.02653 -0.0561 0.8897 0.0339
-5.750 -0.3115 0.03397 0.02384 -0.0576 0.8792 0.0355
-5.500 -0.2735 0.03181 0.02130 -0.0589 0.8685 0.0382
-5.250 -0.2392 0.03027 0.01958 -0.0599 0.8567 0.0429
-5.000 -0.2044 0.02895 0.01815 -0.0611 0.8462 0.0486
-4.750 -0.1746 0.02799 0.01703 -0.0615 0.8337 0.0558
-4.500 -0.1476 0.02718 0.01587 -0.0612 0.8211 0.0650
-4.250 -0.1219 0.02623 0.01484 -0.0610 0.8100 0.0753
-4.000 -0.0981 0.02549 0.01408 -0.0605 0.7986 0.0908
-3.750 -0.0779 0.02460 0.01337 -0.0596 0.7874 0.1223
-3.500 -0.0637 0.02290 0.01270 -0.0581 0.7788 0.3062
-3.250 -0.0555 0.02193 0.01294 -0.0540 0.7685 0.5450
-3.000 -0.0044 0.02257 0.01401 -0.0539 0.7622 0.7366
-2.750 0.0226 0.02310 0.01430 -0.0527 0.7527 0.7788
-2.500 0.0545 0.02373 0.01463 -0.0519 0.7454 0.8221
-2.250 0.0878 0.02449 0.01514 -0.0515 0.7366 0.8631
-2.000 0.1441 0.02495 0.01525 -0.0555 0.7296 0.8984
-1.750 0.1923 0.02506 0.01508 -0.0592 0.7221 0.9198
-1.500 0.2381 0.02502 0.01477 -0.0628 0.7149 0.9381
-1.250 0.2872 0.02487 0.01436 -0.0672 0.7087 0.9557
-1.000 0.3314 0.02472 0.01404 -0.0711 0.7002 0.9701
-0.750 0.3771 0.02440 0.01347 -0.0751 0.6934 0.9806
-0.500 0.4153 0.02427 0.01323 -0.0782 0.6843 0.9905
-0.250 0.4560 0.02405 0.01282 -0.0814 0.6774 0.9992
0.000 0.4744 0.02426 0.01298 -0.0805 0.6698 1.0000
0.250 0.4929 0.02445 0.01308 -0.0795 0.6633 1.0000
0.500 0.5135 0.02460 0.01311 -0.0786 0.6583 1.0000
0.750 0.5277 0.02504 0.01357 -0.0771 0.6512 1.0000
1.000 0.5461 0.02529 0.01376 -0.0759 0.6455 1.0000
1.250 0.5653 0.02555 0.01395 -0.0748 0.6404 1.0000
1.500 0.5781 0.02607 0.01451 -0.0729 0.6331 1.0000
1.750 0.5967 0.02637 0.01475 -0.0717 0.6278 1.0000
2.000 0.6135 0.02676 0.01511 -0.0702 0.6223 1.0000
2.250 0.6253 0.02737 0.01576 -0.0681 0.6155 1.0000
2.500 0.6446 0.02764 0.01598 -0.0668 0.6102 1.0000
2.750 0.6574 0.02819 0.01658 -0.0647 0.6036 1.0000
3.000 0.6698 0.02872 0.01713 -0.0626 0.5965 1.0000
3.250 0.6920 0.02886 0.01722 -0.0615 0.5917 1.0000
3.500 0.6949 0.02982 0.01827 -0.0582 0.5837 1.0000
3.750 0.7092 0.03035 0.01883 -0.0563 0.5784 1.0000
4.000 0.7310 0.03062 0.01912 -0.0553 0.5747 1.0000
4.250 0.7252 0.03198 0.02060 -0.0510 0.5668 1.0000
4.500 0.7388 0.03256 0.02122 -0.0490 0.5618 1.0000
4.750 0.7629 0.03273 0.02140 -0.0482 0.5582 1.0000
5.000 0.7483 0.03434 0.02312 -0.0428 0.5490 1.0000
5.250 0.7700 0.03448 0.02331 -0.0415 0.5438 1.0000
5.500 0.7655 0.03565 0.02455 -0.0373 0.5359 1.0000
5.750 0.7723 0.03639 0.02535 -0.0344 0.5292 1.0000
6.000 0.8018 0.03629 0.02532 -0.0341 0.5252 1.0000
6.250 0.7713 0.03865 0.02775 -0.0274 0.5146 1.0000
6.500 0.7963 0.03876 0.02794 -0.0267 0.5100 1.0000
6.750 0.7728 0.04120 0.03043 -0.0217 0.4998 1.0000
7.000 0.7942 0.04155 0.03088 -0.0208 0.4944 1.0000
7.250 0.7754 0.04404 0.03341 -0.0169 0.4844 1.0000
7.500 0.7982 0.04417 0.03365 -0.0160 0.4778 1.0000
7.750 0.7863 0.04674 0.03628 -0.0136 0.4671 1.0000
8.000 0.8175 0.04596 0.03563 -0.0128 0.4601 1.0000
8.250 0.8039 0.04902 0.03875 -0.0112 0.4477 1.0000
8.500 0.8529 0.04628 0.03617 -0.0103 0.4418 1.0000
8.750 0.8354 0.04984 0.03980 -0.0090 0.4286 1.0000
9.000 0.8931 0.04612 0.03629 -0.0080 0.4240 1.0000
9.250 0.8688 0.05052 0.04076 -0.0070 0.4101 1.0000
9.750 0.8885 0.05306 0.04359 -0.0056 0.3919 1.0000
10.250 0.9081 0.05578 0.04662 -0.0044 0.3743 1.0000
10.750 0.9005 0.06178 0.05287 -0.0042 0.3505 1.0000
11.500 0.9343 0.06527 0.05690 -0.0028 0.3214 1.0000
11.750 0.9428 0.06676 0.05858 -0.0025 0.3105 1.0000
12.250 0.9556 0.07027 0.06245 -0.0020 0.2864 1.0000
12.500 0.9752 0.06998 0.06238 -0.0011 0.2740 1.0000
12.750 0.9730 0.07300 0.06555 -0.0014 0.2585 1.0000
13.000 0.9807 0.07445 0.06717 -0.0011 0.2420 1.0000
13.250 1.0101 0.07198 0.06467 0.0009 0.2171 1.0000
13.500 0.9975 0.07665 0.06943 -0.0002 0.1948 1.0000
13.750 1.0048 0.07766 0.07009 0.0003 0.1681 1.0000
14.000 0.9973 0.08182 0.07424 -0.0007 0.1474 1.0000
14.250 0.9957 0.08488 0.07704 -0.0013 0.1325 1.0000
14.500 0.9923 0.08854 0.08058 -0.0021 0.1193 1.0000
14.750 0.9875 0.09281 0.08493 -0.0035 0.1062 1.0000
15.000 0.9858 0.09645 0.08848 -0.0046 0.0975 1.0000
15.250 0.9869 0.09962 0.09155 -0.0053 0.0903 1.0000
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Polar data table (+)
Polar graphs
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