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WORTMANN FX 80-080 (fx80080-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
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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