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EPPLER 552 AIRFOIL (e552-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 552 AIRFOIL (e552-il)
Reynolds number: 500,000
Max Cl/Cd: 100.49 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e552-il-500000-n5.txt
Download as CSV file: xf-e552-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 552 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -18.500  -0.6824   0.13818   0.13510  -0.0265   1.0000   0.0049
 -18.250  -0.7024   0.12935   0.12614  -0.0310   1.0000   0.0049
 -18.000  -0.7242   0.12052   0.11717  -0.0354   1.0000   0.0049
 -17.750  -0.7396   0.11331   0.10985  -0.0390   1.0000   0.0048
 -17.500  -0.7563   0.10593   0.10231  -0.0428   1.0000   0.0049
 -17.250  -0.7693   0.09959   0.09586  -0.0459   1.0000   0.0048
 -17.000  -0.7813   0.09362   0.08977  -0.0489   1.0000   0.0048
 -16.750  -0.7902   0.08836   0.08439  -0.0514   1.0000   0.0048
 -16.500  -0.7991   0.08324   0.07915  -0.0538   1.0000   0.0049
 -16.250  -0.8051   0.07878   0.07459  -0.0558   1.0000   0.0049
 -16.000  -0.8100   0.07460   0.07030  -0.0576   1.0000   0.0049
 -15.750  -0.8144   0.07063   0.06622  -0.0592   1.0000   0.0049
 -15.500  -0.8174   0.06699   0.06250  -0.0606   1.0000   0.0049
 -15.250  -0.8194   0.06357   0.05898  -0.0618   1.0000   0.0050
 -15.000  -0.8205   0.06040   0.05572  -0.0628   1.0000   0.0050
 -14.750  -0.8210   0.05739   0.05263  -0.0636   1.0000   0.0050
 -14.500  -0.8200   0.05465   0.04980  -0.0643   1.0000   0.0050
 -14.250  -0.8191   0.05200   0.04707  -0.0648   1.0000   0.0050
 -14.000  -0.8188   0.04939   0.04440  -0.0652   1.0000   0.0051
 -13.750  -0.8200   0.04677   0.04171  -0.0654   1.0000   0.0052
 -13.500  -0.8202   0.04438   0.03925  -0.0655   1.0000   0.0053
 -13.250  -0.8178   0.04231   0.03712  -0.0654   1.0000   0.0052
 -13.000  -0.8159   0.04026   0.03502  -0.0652   1.0000   0.0054
 -12.750  -0.8131   0.03834   0.03306  -0.0648   1.0000   0.0054
 -12.500  -0.8111   0.03643   0.03110  -0.0644   1.0000   0.0055
 -12.250  -0.8026   0.03465   0.02927  -0.0647   0.9993   0.0056
 -12.000  -0.7892   0.03285   0.02743  -0.0656   0.9868   0.0058
 -11.750  -0.7343   0.03036   0.02482  -0.0757   0.9311   0.0061
 -11.500  -0.6398   0.02785   0.02202  -0.0935   0.8847   0.0067
 -11.250  -0.6138   0.02670   0.02054  -0.0962   0.8217   0.0069
 -11.000  -0.6063   0.02559   0.01922  -0.0952   0.7873   0.0071
 -10.750  -0.6008   0.02436   0.01784  -0.0941   0.7617   0.0072
 -10.500  -0.5951   0.02311   0.01647  -0.0930   0.7414   0.0075
 -10.250  -0.5877   0.02199   0.01524  -0.0919   0.7247   0.0077
 -10.000  -0.5804   0.02089   0.01403  -0.0907   0.7101   0.0080
  -9.750  -0.5730   0.01989   0.01293  -0.0893   0.6971   0.0084
  -9.500  -0.5695   0.01896   0.01189  -0.0872   0.6851   0.0087
  -9.250  -0.5606   0.01825   0.01108  -0.0855   0.6739   0.0092
  -9.000  -0.5467   0.01763   0.01037  -0.0843   0.6636   0.0096
  -8.500  -0.5126   0.01655   0.00913  -0.0822   0.6434   0.0115
  -8.250  -0.4935   0.01605   0.00856  -0.0814   0.6348   0.0131
  -8.000  -0.4726   0.01562   0.00807  -0.0808   0.6262   0.0149
  -7.750  -0.4512   0.01519   0.00759  -0.0803   0.6188   0.0180
  -7.500  -0.4287   0.01478   0.00715  -0.0798   0.6114   0.0221
  -7.250  -0.4059   0.01439   0.00673  -0.0794   0.6046   0.0276
  -7.000  -0.3822   0.01399   0.00633  -0.0792   0.5980   0.0351
  -6.750  -0.3586   0.01359   0.00593  -0.0789   0.5915   0.0457
  -6.500  -0.3346   0.01316   0.00554  -0.0787   0.5855   0.0619
  -6.250  -0.3105   0.01269   0.00514  -0.0786   0.5793   0.0858
  -5.750  -0.2628   0.01149   0.00425  -0.0785   0.5683   0.1729
  -5.500  -0.2404   0.01049   0.00362  -0.0786   0.5633   0.2664
  -5.250  -0.2161   0.00980   0.00328  -0.0787   0.5586   0.3627
  -5.000  -0.1881   0.00969   0.00320  -0.0789   0.5543   0.3922
  -4.750  -0.1595   0.00965   0.00314  -0.0790   0.5499   0.4101
  -4.500  -0.1310   0.00966   0.00310  -0.0792   0.5455   0.4248
  -4.000  -0.0736   0.00970   0.00303  -0.0795   0.5374   0.4441
  -3.750  -0.0449   0.00975   0.00306  -0.0796   0.5333   0.4561
  -3.500  -0.0160   0.00983   0.00303  -0.0798   0.5295   0.4639
  -3.250   0.0125   0.00981   0.00297  -0.0800   0.5262   0.4661
  -3.000   0.0413   0.00980   0.00291  -0.0802   0.5232   0.4681
  -2.750   0.0702   0.00978   0.00286  -0.0804   0.5201   0.4700
  -2.500   0.0990   0.00978   0.00281  -0.0806   0.5169   0.4719
  -2.250   0.1278   0.00979   0.00277  -0.0808   0.5139   0.4742
  -2.000   0.1564   0.00982   0.00273  -0.0809   0.5109   0.4764
  -1.750   0.1852   0.00984   0.00269  -0.0812   0.5081   0.4783
  -1.500   0.2142   0.00984   0.00266  -0.0814   0.5053   0.4800
  -1.250   0.2430   0.00983   0.00265  -0.0816   0.5026   0.4818
  -1.000   0.2716   0.00984   0.00265  -0.0818   0.5000   0.4837
  -0.750   0.3003   0.00986   0.00265  -0.0820   0.4976   0.4858
  -0.500   0.3288   0.00991   0.00266  -0.0822   0.4952   0.4882
  -0.250   0.3574   0.00995   0.00268  -0.0824   0.4929   0.4905
   0.000   0.3863   0.00997   0.00269  -0.0826   0.4905   0.4926
   0.250   0.4152   0.01000   0.00271  -0.0828   0.4880   0.4946
   0.500   0.4438   0.01003   0.00274  -0.0830   0.4857   0.4966
   0.750   0.4723   0.01006   0.00278  -0.0832   0.4835   0.4986
   1.000   0.5007   0.01010   0.00282  -0.0834   0.4813   0.5009
   1.250   0.5290   0.01017   0.00287  -0.0835   0.4790   0.5035
   1.500   0.5575   0.01023   0.00294  -0.0837   0.4769   0.5063
   1.750   0.5862   0.01027   0.00300  -0.0840   0.4749   0.5090
   2.000   0.6148   0.01032   0.00306  -0.0842   0.4726   0.5114
   2.250   0.6432   0.01036   0.00313  -0.0843   0.4701   0.5137
   2.500   0.6714   0.01041   0.00321  -0.0845   0.4678   0.5162
   2.750   0.6995   0.01048   0.00329  -0.0846   0.4656   0.5190
   3.000   0.7274   0.01057   0.00339  -0.0847   0.4633   0.5220
   3.250   0.7556   0.01065   0.00349  -0.0849   0.4611   0.5251
   3.750   0.8120   0.01075   0.00370  -0.0852   0.4559   0.5315
   4.000   0.8397   0.01082   0.00380  -0.0853   0.4528   0.5350
   4.250   0.8673   0.01090   0.00391  -0.0853   0.4498   0.5386
   4.500   0.8945   0.01102   0.00402  -0.0853   0.4467   0.5422
   4.750   0.9224   0.01107   0.00415  -0.0855   0.4436   0.5456
   5.000   0.9500   0.01113   0.00429  -0.0855   0.4402   0.5494
   5.250   0.9772   0.01122   0.00442  -0.0855   0.4366   0.5536
   5.500   1.0039   0.01133   0.00454  -0.0854   0.4327   0.5579
   5.750   1.0310   0.01141   0.00469  -0.0854   0.4286   0.5624
   6.000   1.0580   0.01148   0.00485  -0.0854   0.4240   0.5674
   6.250   1.0843   0.01159   0.00500  -0.0852   0.4194   0.5729
   6.500   1.1104   0.01171   0.00516  -0.0851   0.4150   0.5781
   6.750   1.1370   0.01179   0.00534  -0.0850   0.4094   0.5835
   7.000   1.1623   0.01192   0.00551  -0.0846   0.4030   0.5895
   7.250   1.1880   0.01204   0.00569  -0.0844   0.3963   0.5953
   7.500   1.2124   0.01219   0.00589  -0.0840   0.3878   0.6018
   7.750   1.2370   0.01234   0.00610  -0.0836   0.3783   0.6088
   8.000   1.2601   0.01254   0.00634  -0.0829   0.3674   0.6163
   8.250   1.2819   0.01280   0.00662  -0.0820   0.3541   0.6246
   8.500   1.3017   0.01313   0.00695  -0.0809   0.3365   0.6330
   8.750   1.3189   0.01357   0.00735  -0.0793   0.3167   0.6418
   9.000   1.3327   0.01413   0.00786  -0.0772   0.2951   0.6508
   9.250   1.3427   0.01475   0.00842  -0.0745   0.2729   0.6603
   9.500   1.3483   0.01545   0.00907  -0.0710   0.2526   0.6707
   9.750   1.3545   0.01619   0.00979  -0.0678   0.2337   0.6819
  10.000   1.3583   0.01705   0.01062  -0.0644   0.2149   0.6944
  10.250   1.3613   0.01797   0.01153  -0.0612   0.1985   0.7093
  10.500   1.3624   0.01903   0.01260  -0.0579   0.1831   0.7262
  10.750   1.3636   0.02016   0.01378  -0.0550   0.1702   0.7459
  11.000   1.3641   0.02145   0.01512  -0.0523   0.1588   0.7702
  11.750   1.3629   0.02609   0.02018  -0.0459   0.1298   1.0000
  12.000   1.3629   0.02817   0.02226  -0.0446   0.1215   1.0000
  12.250   1.3609   0.03051   0.02460  -0.0435   0.1124   1.0000
  12.500   1.3604   0.03284   0.02694  -0.0426   0.1041   1.0000
  12.750   1.3575   0.03546   0.02956  -0.0418   0.0964   1.0000
  13.000   1.3570   0.03793   0.03205  -0.0412   0.0898   1.0000
  13.250   1.3532   0.04076   0.03489  -0.0406   0.0821   1.0000
  13.500   1.3499   0.04362   0.03775  -0.0402   0.0756   1.0000
  13.750   1.3473   0.04649   0.04064  -0.0399   0.0684   1.0000
  14.000   1.3443   0.04950   0.04365  -0.0397   0.0628   1.0000
  14.250   1.3429   0.05243   0.04659  -0.0397   0.0566   1.0000
  14.500   1.3417   0.05540   0.04959  -0.0397   0.0520   1.0000
  14.750   1.3431   0.05816   0.05238  -0.0399   0.0483   1.0000
  15.000   1.3423   0.06124   0.05548  -0.0402   0.0447   1.0000
  15.250   1.3442   0.06407   0.05836  -0.0405   0.0417   1.0000
  15.500   1.3444   0.06714   0.06146  -0.0409   0.0383   1.0000
  15.750   1.3446   0.07028   0.06464  -0.0414   0.0357   1.0000
  16.000   1.3470   0.07318   0.06760  -0.0419   0.0333   1.0000
  16.250   1.3467   0.07651   0.07098  -0.0426   0.0308   1.0000
  16.500   1.3471   0.07976   0.07427  -0.0433   0.0283   1.0000
  16.750   1.3475   0.08308   0.07763  -0.0441   0.0260   1.0000
  17.250   1.3485   0.08986   0.08453  -0.0460   0.0229   1.0000
  17.500   1.3483   0.09341   0.08811  -0.0470   0.0207   1.0000
  17.750   1.3483   0.09696   0.09173  -0.0482   0.0198   1.0000
  18.000   1.3482   0.10059   0.09542  -0.0494   0.0183   1.0000
  18.250   1.3480   0.10426   0.09915  -0.0507   0.0168   1.0000
  18.500   1.3456   0.10833   0.10326  -0.0522   0.0154   1.0000
  18.750   1.3459   0.11199   0.10701  -0.0536   0.0144   1.0000
  19.000   1.3451   0.11587   0.11097  -0.0551   0.0135   1.0000
  19.250   1.3440   0.11980   0.11496  -0.0568   0.0125   1.0000
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