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EPPLER 554 AIRFOIL (e554-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 554 AIRFOIL (e554-il)
Reynolds number: 200,000
Max Cl/Cd: 70.18 at α=9.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e554-il-200000-n5.txt
Download as CSV file: xf-e554-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 554 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.500  -0.5705   0.12995   0.12582  -0.0338   1.0000   0.0113
 -16.250  -0.6173   0.11430   0.10993  -0.0420   1.0000   0.0109
 -16.000  -0.6457   0.10403   0.09946  -0.0476   1.0000   0.0108
 -15.750  -0.6682   0.09570   0.09092  -0.0521   1.0000   0.0108
 -15.500  -0.6823   0.08940   0.08446  -0.0553   1.0000   0.0107
 -15.250  -0.6972   0.08324   0.07811  -0.0584   1.0000   0.0109
 -15.000  -0.7060   0.07837   0.07308  -0.0607   1.0000   0.0109
 -14.750  -0.7145   0.07375   0.06830  -0.0626   1.0000   0.0110
 -14.500  -0.7195   0.06982   0.06423  -0.0641   1.0000   0.0111
 -14.250  -0.7250   0.06594   0.06017  -0.0654   1.0000   0.0113
 -14.000  -0.7265   0.06276   0.05686  -0.0662   1.0000   0.0113
 -13.750  -0.7270   0.05982   0.05378  -0.0668   1.0000   0.0115
 -13.500  -0.7267   0.05708   0.05088  -0.0670   1.0000   0.0116
 -13.250  -0.7242   0.05480   0.04856  -0.0671   1.0000   0.0118
 -13.000  -0.7210   0.05265   0.04636  -0.0671   1.0000   0.0118
 -12.750  -0.7183   0.05054   0.04422  -0.0670   1.0000   0.0121
 -12.500  -0.7153   0.04851   0.04215  -0.0668   1.0000   0.0123
 -12.250  -0.7112   0.04665   0.04024  -0.0664   1.0000   0.0125
 -12.000  -0.7078   0.04479   0.03833  -0.0659   1.0000   0.0128
 -11.750  -0.7044   0.04300   0.03650  -0.0653   1.0000   0.0131
 -11.500  -0.7009   0.04130   0.03474  -0.0645   1.0000   0.0134
 -11.250  -0.6978   0.03967   0.03306  -0.0635   1.0000   0.0137
 -11.000  -0.6954   0.03806   0.03140  -0.0624   1.0000   0.0140
 -10.750  -0.6951   0.03642   0.02972  -0.0611   1.0000   0.0144
 -10.500  -0.6964   0.03481   0.02813  -0.0595   1.0000   0.0147
 -10.250  -0.6954   0.03328   0.02659  -0.0583   0.9994   0.0151
 -10.000  -0.6702   0.03137   0.02462  -0.0617   0.9876   0.0163
  -9.750  -0.6553   0.02959   0.02277  -0.0630   0.9611   0.0173
  -9.500  -0.6292   0.02771   0.02085  -0.0666   0.9375   0.0188
  -9.250  -0.5933   0.02564   0.01865  -0.0724   0.9152   0.0210
  -9.000  -0.5495   0.02357   0.01641  -0.0796   0.8908   0.0242
  -8.750  -0.5099   0.02186   0.01453  -0.0855   0.8628   0.0283
  -8.500  -0.4810   0.02062   0.01318  -0.0883   0.8349   0.0340
  -8.250  -0.4586   0.01966   0.01210  -0.0892   0.8097   0.0409
  -8.000  -0.4389   0.01886   0.01120  -0.0893   0.7880   0.0502
  -7.750  -0.4209   0.01807   0.01037  -0.0889   0.7685   0.0637
  -7.500  -0.4023   0.01731   0.00960  -0.0884   0.7516   0.0828
  -7.250  -0.3835   0.01648   0.00883  -0.0880   0.7363   0.1126
  -6.750  -0.3471   0.01428   0.00709  -0.0877   0.7086   0.2371
  -6.500  -0.3255   0.01358   0.00674  -0.0876   0.6959   0.3296
  -6.250  -0.2992   0.01352   0.00664  -0.0874   0.6835   0.3670
  -6.000  -0.2720   0.01354   0.00657  -0.0873   0.6719   0.3894
  -5.750  -0.2446   0.01362   0.00652  -0.0872   0.6615   0.4065
  -5.500  -0.2171   0.01371   0.00649  -0.0870   0.6513   0.4197
  -5.250  -0.1893   0.01377   0.00637  -0.0870   0.6420   0.4305
  -5.000  -0.1617   0.01392   0.00643  -0.0868   0.6325   0.4406
  -4.750  -0.1341   0.01413   0.00656  -0.0866   0.6236   0.4522
  -4.500  -0.1063   0.01425   0.00650  -0.0865   0.6147   0.4616
  -4.250  -0.0785   0.01420   0.00634  -0.0865   0.6067   0.4647
  -4.000  -0.0507   0.01417   0.00622  -0.0865   0.5989   0.4674
  -3.750  -0.0228   0.01415   0.00609  -0.0865   0.5922   0.4703
  -3.500   0.0053   0.01410   0.00594  -0.0866   0.5851   0.4733
  -3.250   0.0334   0.01407   0.00577  -0.0867   0.5787   0.4768
  -3.000   0.0619   0.01403   0.00558  -0.0869   0.5724   0.4801
  -2.750   0.0898   0.01399   0.00550  -0.0869   0.5658   0.4821
  -2.500   0.1176   0.01399   0.00541  -0.0869   0.5601   0.4845
  -2.250   0.1458   0.01398   0.00536  -0.0870   0.5544   0.4873
  -2.000   0.1741   0.01398   0.00529  -0.0871   0.5490   0.4905
  -1.750   0.2023   0.01399   0.00520  -0.0872   0.5442   0.4935
  -1.500   0.2308   0.01400   0.00511  -0.0874   0.5396   0.4965
  -1.250   0.2590   0.01399   0.00508  -0.0875   0.5344   0.4990
  -1.000   0.2869   0.01401   0.00507  -0.0876   0.5295   0.5015
  -0.750   0.3149   0.01406   0.00506  -0.0876   0.5253   0.5045
  -0.500   0.3432   0.01409   0.00508  -0.0878   0.5212   0.5076
  -0.250   0.3716   0.01412   0.00508  -0.0879   0.5169   0.5107
   0.000   0.4000   0.01417   0.00507  -0.0881   0.5129   0.5139
   0.250   0.4280   0.01423   0.00508  -0.0882   0.5092   0.5166
   0.500   0.4560   0.01428   0.00514  -0.0883   0.5055   0.5193
   0.750   0.4839   0.01434   0.00522  -0.0883   0.5013   0.5225
   1.000   0.5120   0.01440   0.00529  -0.0884   0.4977   0.5261
   1.250   0.5402   0.01449   0.00534  -0.0886   0.4944   0.5298
   1.500   0.5685   0.01459   0.00539  -0.0888   0.4912   0.5332
   1.750   0.5962   0.01466   0.00551  -0.0888   0.4878   0.5360
   2.000   0.6238   0.01474   0.00564  -0.0888   0.4840   0.5391
   2.250   0.6516   0.01483   0.00577  -0.0889   0.4807   0.5428
   2.500   0.6795   0.01494   0.00588  -0.0890   0.4775   0.5471
   2.750   0.7076   0.01508   0.00597  -0.0891   0.4745   0.5513
   3.000   0.7350   0.01518   0.00615  -0.0891   0.4714   0.5548
   3.250   0.7623   0.01529   0.00635  -0.0891   0.4680   0.5586
   3.500   0.7896   0.01541   0.00652  -0.0891   0.4645   0.5629
   3.750   0.8171   0.01554   0.00667  -0.0892   0.4612   0.5674
   4.000   0.8446   0.01568   0.00683  -0.0892   0.4583   0.5714
   4.250   0.8720   0.01584   0.00703  -0.0892   0.4555   0.5761
   4.500   0.8985   0.01598   0.00729  -0.0891   0.4519   0.5814
   4.750   0.9253   0.01613   0.00751  -0.0891   0.4483   0.5868
   5.000   0.9519   0.01626   0.00773  -0.0889   0.4449   0.5914
   5.250   0.9788   0.01642   0.00794  -0.0889   0.4418   0.5968
   5.500   1.0059   0.01662   0.00815  -0.0889   0.4387   0.6029
   5.750   1.0312   0.01677   0.00848  -0.0885   0.4346   0.6085
   6.000   1.0567   0.01693   0.00875  -0.0883   0.4305   0.6153
   6.250   1.0826   0.01709   0.00896  -0.0880   0.4265   0.6224
   6.500   1.1089   0.01726   0.00917  -0.0879   0.4228   0.6290
   6.750   1.1326   0.01743   0.00951  -0.0873   0.4178   0.6367
   7.000   1.1568   0.01758   0.00979  -0.0867   0.4127   0.6441
   7.250   1.1816   0.01774   0.01002  -0.0863   0.4083   0.6531
   7.500   1.2054   0.01793   0.01034  -0.0857   0.4034   0.6623
   7.750   1.2282   0.01811   0.01067  -0.0850   0.3976   0.6728
   8.000   1.2512   0.01826   0.01092  -0.0843   0.3921   0.6831
   8.250   1.2731   0.01846   0.01126  -0.0834   0.3858   0.6946
   8.500   1.2942   0.01865   0.01158  -0.0824   0.3789   0.7074
   8.750   1.3149   0.01884   0.01188  -0.0812   0.3726   0.7217
   9.000   1.3341   0.01905   0.01228  -0.0799   0.3645   0.7378
   9.250   1.3523   0.01927   0.01259  -0.0784   0.3569   0.7564
   9.750   1.3827   0.01977   0.01340  -0.0744   0.3379   0.8042
  10.000   1.3907   0.02001   0.01376  -0.0710   0.3278   0.8429
  10.250   1.3963   0.02018   0.01414  -0.0672   0.3170   1.0000
  10.500   1.4063   0.02077   0.01473  -0.0649   0.3043   1.0000
  10.750   1.4133   0.02151   0.01546  -0.0622   0.2902   1.0000
  11.000   1.4175   0.02244   0.01637  -0.0595   0.2755   1.0000
  11.250   1.4192   0.02359   0.01749  -0.0568   0.2608   1.0000
  11.500   1.4180   0.02502   0.01889  -0.0541   0.2457   1.0000
  11.750   1.4152   0.02673   0.02058  -0.0517   0.2313   1.0000
  12.000   1.4102   0.02879   0.02261  -0.0496   0.2171   1.0000
  12.250   1.4040   0.03115   0.02495  -0.0479   0.2041   1.0000
  12.500   1.3972   0.03378   0.02759  -0.0465   0.1915   1.0000
  12.750   1.3909   0.03658   0.03039  -0.0455   0.1795   1.0000
  13.000   1.3840   0.03960   0.03342  -0.0448   0.1686   1.0000
  13.250   1.3760   0.04286   0.03669  -0.0443   0.1588   1.0000
  13.500   1.3682   0.04623   0.04008  -0.0441   0.1492   1.0000
  13.750   1.3622   0.04955   0.04344  -0.0440   0.1402   1.0000
  14.000   1.3543   0.05319   0.04709  -0.0441   0.1320   1.0000
  14.250   1.3480   0.05680   0.05073  -0.0444   0.1234   1.0000
  14.500   1.3427   0.06039   0.05435  -0.0448   0.1160   1.0000
  14.750   1.3358   0.06432   0.05829  -0.0454   0.1087   1.0000
  15.000   1.3323   0.06790   0.06193  -0.0460   0.1015   1.0000
  15.250   1.3259   0.07195   0.06600  -0.0468   0.0953   1.0000
  15.500   1.3235   0.07560   0.06970  -0.0477   0.0888   1.0000
  15.750   1.3185   0.07965   0.07377  -0.0487   0.0831   1.0000
  16.000   1.3160   0.08342   0.07759  -0.0497   0.0773   1.0000
  16.250   1.3118   0.08752   0.08173  -0.0509   0.0724   1.0000
  16.500   1.3096   0.09139   0.08566  -0.0520   0.0674   1.0000
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