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EPPLER 558 AIRFOIL (e558-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 558 AIRFOIL (e558-il)
Reynolds number: 100,000
Max Cl/Cd: 41.16 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e558-il-100000.txt
Download as CSV file: xf-e558-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 558 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.6076   0.07248   0.06695  -0.0730   1.0000   0.0542
 -12.000  -0.6321   0.06646   0.06084  -0.0763   1.0000   0.0538
 -11.750  -0.6599   0.06083   0.05509  -0.0793   1.0000   0.0535
 -11.500  -0.6841   0.05646   0.05061  -0.0809   1.0000   0.0533
 -11.250  -0.7099   0.05297   0.04701  -0.0808   1.0000   0.0532
 -11.000  -0.7325   0.05031   0.04425  -0.0792   1.0000   0.0530
 -10.750  -0.7482   0.04750   0.04123  -0.0775   1.0000   0.0532
 -10.500  -0.7596   0.04486   0.03832  -0.0757   1.0000   0.0538
 -10.250  -0.7655   0.04245   0.03557  -0.0738   1.0000   0.0544
 -10.000  -0.7572   0.04032   0.03356  -0.0722   1.0000   0.0562
  -9.750  -0.7510   0.03873   0.03194  -0.0704   1.0000   0.0581
  -9.500  -0.7448   0.03694   0.03000  -0.0686   1.0000   0.0600
  -9.250  -0.7380   0.03506   0.02787  -0.0668   1.0000   0.0621
  -9.000  -0.7282   0.03328   0.02607  -0.0650   1.0000   0.0644
  -8.750  -0.7175   0.03200   0.02487  -0.0633   1.0000   0.0679
  -8.500  -0.7065   0.03062   0.02325  -0.0619   1.0000   0.0727
  -8.250  -0.6954   0.02937   0.02219  -0.0605   1.0000   0.0798
  -8.000  -0.6833   0.02805   0.02092  -0.0595   1.0000   0.0891
  -7.750  -0.6700   0.02673   0.01965  -0.0587   1.0000   0.1038
  -7.500  -0.6556   0.02555   0.01859  -0.0583   1.0000   0.1261
  -7.250  -0.6174   0.02493   0.01794  -0.0622   0.9941   0.1640
  -7.000  -0.5703   0.02509   0.01820  -0.0669   0.9844   0.1978
  -6.750  -0.5253   0.02551   0.01859  -0.0708   0.9740   0.2252
  -6.500  -0.4821   0.02581   0.01894  -0.0739   0.9634   0.2471
  -6.250  -0.4397   0.02611   0.01928  -0.0766   0.9531   0.2662
  -6.000  -0.3921   0.02627   0.01942  -0.0801   0.9449   0.2848
  -5.750  -0.3545   0.02617   0.01926  -0.0819   0.9333   0.3001
  -5.500  -0.3152   0.02596   0.01895  -0.0840   0.9225   0.3152
  -5.250  -0.2673   0.02566   0.01854  -0.0875   0.9153   0.3311
  -5.000  -0.2313   0.02550   0.01834  -0.0887   0.9035   0.3437
  -4.750  -0.1806   0.02511   0.01793  -0.0923   0.8981   0.3571
  -4.500  -0.1457   0.02468   0.01741  -0.0935   0.8861   0.3692
  -4.250  -0.0921   0.02398   0.01654  -0.0980   0.8812   0.3842
  -4.000  -0.0578   0.02372   0.01629  -0.0987   0.8689   0.3943
  -3.750  -0.0070   0.02302   0.01549  -0.1024   0.8631   0.4072
  -3.500   0.0263   0.02256   0.01482  -0.1035   0.8496   0.4195
  -3.250   0.0627   0.02223   0.01453  -0.1044   0.8382   0.4289
  -3.000   0.1048   0.02164   0.01379  -0.1068   0.8284   0.4409
  -2.750   0.1348   0.02141   0.01349  -0.1068   0.8142   0.4512
  -2.500   0.1662   0.02111   0.01312  -0.1072   0.8012   0.4611
  -2.250   0.2019   0.02079   0.01260  -0.1084   0.7899   0.4733
  -2.000   0.2297   0.02061   0.01244  -0.1079   0.7762   0.4820
  -1.750   0.2573   0.02047   0.01215  -0.1078   0.7625   0.4935
  -1.500   0.2859   0.02035   0.01201  -0.1076   0.7504   0.5028
  -1.250   0.3165   0.02017   0.01170  -0.1078   0.7388   0.5142
  -1.000   0.3411   0.02016   0.01167  -0.1070   0.7254   0.5249
  -0.750   0.3685   0.02009   0.01156  -0.1067   0.7139   0.5354
  -0.500   0.3982   0.02000   0.01133  -0.1068   0.7031   0.5483
  -0.250   0.4217   0.02004   0.01143  -0.1058   0.6908   0.5588
   0.000   0.4501   0.02001   0.01133  -0.1057   0.6808   0.5711
   0.250   0.4762   0.02003   0.01130  -0.1053   0.6696   0.5847
   0.500   0.5011   0.02010   0.01140  -0.1045   0.6591   0.5971
   0.750   0.5292   0.02008   0.01135  -0.1042   0.6498   0.6108
   1.000   0.5527   0.02021   0.01153  -0.1034   0.6392   0.6254
   1.250   0.5819   0.02021   0.01147  -0.1033   0.6310   0.6418
   1.500   0.6040   0.02038   0.01173  -0.1023   0.6204   0.6584
   1.750   0.6327   0.02040   0.01171  -0.1020   0.6130   0.6771
   2.000   0.6531   0.02061   0.01208  -0.1007   0.6031   0.6964
   2.250   0.6804   0.02063   0.01208  -0.1001   0.5957   0.7194
   2.500   0.7006   0.02086   0.01246  -0.0987   0.5865   0.7457
   2.750   0.7250   0.02089   0.01255  -0.0975   0.5793   0.7760
   3.000   0.7435   0.02106   0.01289  -0.0954   0.5716   0.8146
   3.250   0.7605   0.02102   0.01302  -0.0927   0.5641   0.8698
   3.500   0.8053   0.02097   0.01303  -0.0960   0.5563   1.0000
   3.750   0.8346   0.02147   0.01345  -0.0973   0.5478   1.0000
   4.000   0.8688   0.02178   0.01354  -0.0987   0.5419   1.0000
   4.250   0.8888   0.02245   0.01428  -0.0979   0.5333   1.0000
   4.500   0.9183   0.02278   0.01451  -0.0982   0.5267   1.0000
   4.750   0.9428   0.02338   0.01510  -0.0979   0.5201   1.0000
   5.000   0.9658   0.02395   0.01570  -0.0973   0.5127   1.0000
   5.250   0.9977   0.02424   0.01587  -0.0979   0.5071   1.0000
   5.500   1.0147   0.02509   0.01685  -0.0965   0.4995   1.0000
   5.750   1.0408   0.02555   0.01731  -0.0963   0.4932   1.0000
   6.000   1.0701   0.02601   0.01769  -0.0965   0.4877   1.0000
   6.250   1.0852   0.02690   0.01875  -0.0948   0.4800   1.0000
   6.500   1.1142   0.02726   0.01907  -0.0950   0.4742   1.0000
   6.750   1.1353   0.02804   0.01992  -0.0941   0.4680   1.0000
   7.000   1.1540   0.02880   0.02078  -0.0929   0.4608   1.0000
   7.250   1.1864   0.02903   0.02094  -0.0934   0.4555   1.0000
   7.500   1.1985   0.03016   0.02227  -0.0914   0.4484   1.0000
   7.750   1.2214   0.03072   0.02287  -0.0907   0.4418   1.0000
   8.000   1.2576   0.03087   0.02291  -0.0917   0.4367   1.0000
   8.250   1.2600   0.03230   0.02465  -0.0885   0.4287   1.0000
   8.500   1.2895   0.03252   0.02485  -0.0886   0.4226   1.0000
   8.750   1.3070   0.03339   0.02583  -0.0872   0.4160   1.0000
   9.000   1.3219   0.03421   0.02678  -0.0855   0.4086   1.0000
   9.250   1.3648   0.03386   0.02628  -0.0872   0.4027   1.0000
   9.500   1.3591   0.03556   0.02830  -0.0830   0.3946   1.0000
   9.750   1.3945   0.03528   0.02798  -0.0836   0.3877   1.0000
  10.000   1.4006   0.03650   0.02938  -0.0809   0.3802   1.0000
  10.250   1.4252   0.03661   0.02952  -0.0802   0.3725   1.0000
  10.500   1.4437   0.03714   0.03012  -0.0788   0.3651   1.0000
  10.750   1.4572   0.03765   0.03076  -0.0768   0.3568   1.0000
  11.000   1.4825   0.03773   0.03084  -0.0762   0.3489   1.0000
  11.250   1.4891   0.03841   0.03167  -0.0733   0.3405   1.0000
  11.500   1.5118   0.03842   0.03168  -0.0723   0.3320   1.0000
  11.750   1.5187   0.03891   0.03228  -0.0694   0.3233   1.0000
  12.000   1.5304   0.03921   0.03263  -0.0670   0.3147   1.0000
  12.250   1.5421   0.03929   0.03274  -0.0646   0.3057   1.0000
  12.500   1.5390   0.04029   0.03385  -0.0608   0.2977   1.0000
  12.750   1.5725   0.03945   0.03286  -0.0608   0.2868   1.0000
  13.000   1.5400   0.04196   0.03567  -0.0547   0.2804   1.0000
  13.250   1.5626   0.04162   0.03523  -0.0536   0.2699   1.0000
  13.500   1.5357   0.04436   0.03823  -0.0494   0.2627   1.0000
  13.750   1.5450   0.04494   0.03876  -0.0477   0.2527   1.0000
  14.000   1.5326   0.04719   0.04113  -0.0453   0.2438   1.0000
  14.250   1.5232   0.04952   0.04354  -0.0435   0.2347   1.0000
  14.500   1.5279   0.05062   0.04453  -0.0423   0.2237   1.0000
  14.750   1.5020   0.05497   0.04911  -0.0412   0.2158   1.0000
  15.000   1.1232   0.11815   0.11284  -0.0636   0.2127   1.0000
  15.250   1.1387   0.11833   0.11310  -0.0630   0.2066   1.0000
  15.500   1.1852   0.11211   0.10701  -0.0594   0.2015   1.0000
  15.750   1.4597   0.06864   0.06285  -0.0405   0.1773   1.0000
  16.000   1.4485   0.07267   0.06687  -0.0411   0.1680   1.0000
  16.250   1.4309   0.07794   0.07226  -0.0423   0.1598   1.0000
  16.500   1.4274   0.08121   0.07541  -0.0428   0.1501   1.0000
  16.750   1.4101   0.08686   0.08120  -0.0446   0.1426   1.0000
  17.000   1.4024   0.09112   0.08544  -0.0457   0.1344   1.0000
  17.250   1.4063   0.09347   0.08759  -0.0459   0.1248   1.0000
  17.500   1.3824   0.10078   0.09519  -0.0489   0.1195   1.0000
  17.750   1.3864   0.10323   0.09747  -0.0493   0.1109   1.0000
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