WORTMANN FX 80-080 (fx80080-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 80-080 (fx80080-il) Reynolds number: 50,000 Max Cl/Cd: 36.17 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx80080-il-50000-n5.txt Download as CSV file: xf-fx80080-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 80-080
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4497 0.09911 0.09222 -0.0318 1.0000 0.1039
-8.250 -0.4581 0.09199 0.08515 -0.0382 1.0000 0.0538
-8.000 -0.4564 0.08859 0.08182 -0.0376 1.0000 0.0520
-7.750 -0.4608 0.08495 0.07828 -0.0387 1.0000 0.0513
-7.500 -0.4632 0.08111 0.07452 -0.0403 1.0000 0.0502
-7.250 -0.4664 0.07737 0.07084 -0.0416 1.0000 0.0502
-7.000 -0.4688 0.07362 0.06711 -0.0424 1.0000 0.0490
-6.750 -0.4706 0.06996 0.06344 -0.0429 1.0000 0.0481
-6.500 -0.4717 0.06635 0.05979 -0.0431 1.0000 0.0484
-6.250 -0.4710 0.06264 0.05598 -0.0430 1.0000 0.0472
-6.000 -0.4681 0.05909 0.05228 -0.0428 1.0000 0.0475
-5.750 -0.4624 0.05529 0.04825 -0.0426 1.0000 0.0467
-5.500 -0.4532 0.05126 0.04389 -0.0426 1.0000 0.0453
-5.250 -0.4402 0.04718 0.03933 -0.0425 1.0000 0.0440
-5.000 -0.4241 0.04347 0.03507 -0.0423 1.0000 0.0433
-4.750 -0.4061 0.04026 0.03138 -0.0418 1.0000 0.0431
-4.500 -0.3866 0.03737 0.02805 -0.0413 1.0000 0.0434
-4.250 -0.3658 0.03476 0.02503 -0.0408 1.0000 0.0442
-4.000 -0.3436 0.03248 0.02237 -0.0403 1.0000 0.0454
-3.750 -0.3215 0.03086 0.02034 -0.0397 1.0000 0.0500
-3.500 -0.2971 0.02926 0.01817 -0.0388 1.0000 0.0544
-3.250 -0.2734 0.02745 0.01618 -0.0380 1.0000 0.0574
-3.000 -0.2503 0.02613 0.01470 -0.0369 1.0000 0.0614
-2.750 -0.2271 0.02508 0.01331 -0.0356 1.0000 0.0684
-2.500 -0.2054 0.02420 0.01238 -0.0347 1.0000 0.0827
-2.250 -0.1822 0.02320 0.01131 -0.0340 1.0000 0.0980
-2.000 -0.1585 0.02224 0.01042 -0.0338 1.0000 0.1387
-1.750 -0.1365 0.01939 0.00989 -0.0337 1.0000 0.5363
-1.500 -0.1337 0.01889 0.01013 -0.0259 0.9977 0.8690
-1.250 -0.0872 0.01869 0.00955 -0.0296 0.9925 1.0000
-1.000 -0.0543 0.01895 0.00938 -0.0314 0.9879 1.0000
-0.750 -0.0227 0.01920 0.00923 -0.0329 0.9827 1.0000
-0.500 0.0113 0.01954 0.00926 -0.0349 0.9785 1.0000
-0.250 0.0409 0.01978 0.00927 -0.0360 0.9727 1.0000
0.000 0.0741 0.02013 0.00940 -0.0378 0.9678 1.0000
0.250 0.1053 0.02045 0.00955 -0.0392 0.9624 1.0000
0.500 0.1365 0.02079 0.00971 -0.0406 0.9566 1.0000
0.750 0.1715 0.02119 0.00999 -0.0427 0.9518 1.0000
1.000 0.1990 0.02151 0.01024 -0.0434 0.9449 1.0000
1.250 0.2339 0.02192 0.01060 -0.0454 0.9395 1.0000
1.500 0.2621 0.02227 0.01092 -0.0462 0.9321 1.0000
1.750 0.2975 0.02267 0.01132 -0.0482 0.9260 1.0000
2.000 0.3257 0.02304 0.01171 -0.0489 0.9178 1.0000
2.250 0.3628 0.02344 0.01221 -0.0512 0.9115 1.0000
2.500 0.3903 0.02381 0.01264 -0.0516 0.9019 1.0000
2.750 0.4231 0.02417 0.01311 -0.0530 0.8932 1.0000
3.000 0.4596 0.02449 0.01357 -0.0549 0.8847 1.0000
3.250 0.4894 0.02480 0.01405 -0.0555 0.8734 1.0000
3.500 0.5222 0.02505 0.01455 -0.0565 0.8615 1.0000
3.750 0.5577 0.02516 0.01491 -0.0577 0.8482 1.0000
4.000 0.5972 0.02503 0.01506 -0.0591 0.8325 1.0000
4.250 0.6389 0.02456 0.01492 -0.0601 0.8119 1.0000
4.500 0.6766 0.02371 0.01449 -0.0596 0.7829 1.0000
4.750 0.7102 0.02262 0.01372 -0.0579 0.7449 1.0000
5.000 0.7308 0.02198 0.01333 -0.0545 0.6965 1.0000
5.250 0.7512 0.02139 0.01292 -0.0510 0.6182 1.0000
5.500 0.7812 0.02160 0.01176 -0.0478 0.3702 1.0000
5.750 0.7841 0.02378 0.01294 -0.0442 0.2321 1.0000
6.000 0.7937 0.02579 0.01446 -0.0419 0.1597 1.0000
6.250 0.8088 0.02759 0.01605 -0.0401 0.1262 1.0000
6.500 0.8271 0.02923 0.01761 -0.0389 0.0990 1.0000
6.750 0.8517 0.03103 0.01951 -0.0381 0.0828 1.0000
7.000 0.8769 0.03271 0.02129 -0.0377 0.0677 1.0000
7.250 0.9096 0.03512 0.02387 -0.0380 0.0596 1.0000
7.500 0.9415 0.03788 0.02693 -0.0381 0.0539 1.0000
7.750 0.9645 0.04064 0.03001 -0.0375 0.0477 1.0000
8.000 0.9846 0.04351 0.03346 -0.0363 0.0429 1.0000
8.250 1.0017 0.04686 0.03718 -0.0349 0.0407 1.0000
8.500 1.0144 0.05063 0.04126 -0.0335 0.0391 1.0000
8.750 1.0198 0.05466 0.04579 -0.0311 0.0378 1.0000
9.000 1.0190 0.05847 0.05022 -0.0282 0.0363 1.0000
9.250 1.0141 0.06233 0.05455 -0.0255 0.0350 1.0000
9.500 1.0055 0.06613 0.05873 -0.0230 0.0340 1.0000
9.750 0.9927 0.06981 0.06269 -0.0204 0.0334 1.0000
10.000 0.9768 0.07356 0.06666 -0.0182 0.0334 1.0000
10.250 0.9582 0.07781 0.07109 -0.0171 0.0335 1.0000
10.500 0.9390 0.08251 0.07594 -0.0174 0.0339 1.0000
10.750 0.9194 0.08792 0.08147 -0.0190 0.0343 1.0000
11.000 0.9020 0.09392 0.08755 -0.0218 0.0351 1.0000
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Polar data table (+)
Polar graphs
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