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EPPLER 540 AIRFOIL (e540-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 540 AIRFOIL (e540-il)
Reynolds number: 200,000
Max Cl/Cd: 57.01 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e540-il-200000-n5.txt
Download as CSV file: xf-e540-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 540 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.4722   0.08851   0.08501  -0.0693   1.0000   0.0079
 -12.250  -0.5239   0.07429   0.07059  -0.0762   1.0000   0.0074
 -12.000  -0.5683   0.06616   0.06224  -0.0772   1.0000   0.0072
 -11.500  -0.6141   0.05371   0.04912  -0.0792   0.9874   0.0068
 -11.250  -0.6235   0.04936   0.04448  -0.0798   0.9728   0.0069
 -11.000  -0.6257   0.04546   0.04022  -0.0803   0.9610   0.0068
 -10.750  -0.6212   0.04185   0.03625  -0.0812   0.9515   0.0068
 -10.500  -0.6088   0.03847   0.03248  -0.0826   0.9444   0.0069
 -10.250  -0.5921   0.03556   0.02922  -0.0837   0.9360   0.0069
 -10.000  -0.5682   0.03301   0.02634  -0.0854   0.9294   0.0071
  -9.750  -0.5426   0.03101   0.02409  -0.0869   0.9211   0.0073
  -9.500  -0.5111   0.02909   0.02186  -0.0888   0.9150   0.0074
  -9.250  -0.4821   0.02764   0.02021  -0.0901   0.9066   0.0078
  -9.000  -0.4497   0.02621   0.01858  -0.0917   0.9001   0.0083
  -8.750  -0.4221   0.02509   0.01730  -0.0923   0.8919   0.0086
  -8.500  -0.3941   0.02405   0.01610  -0.0931   0.8850   0.0095
  -8.250  -0.3721   0.02311   0.01505  -0.0928   0.8767   0.0107
  -8.000  -0.3511   0.02232   0.01418  -0.0926   0.8691   0.0113
  -7.750  -0.3309   0.02173   0.01350  -0.0920   0.8612   0.0129
  -7.500  -0.3132   0.02103   0.01268  -0.0909   0.8542   0.0143
  -7.250  -0.2988   0.02025   0.01180  -0.0893   0.8470   0.0158
  -7.000  -0.2830   0.01960   0.01108  -0.0879   0.8411   0.0179
  -6.750  -0.2674   0.01907   0.01049  -0.0863   0.8347   0.0225
  -6.500  -0.2523   0.01844   0.00983  -0.0847   0.8295   0.0311
  -6.250  -0.2419   0.01777   0.00926  -0.0824   0.8232   0.0481
  -5.750  -0.2260   0.01632   0.00817  -0.0770   0.8124   0.1303
  -5.500  -0.2268   0.01557   0.00769  -0.0728   0.8066   0.1881
  -5.250  -0.2339   0.01475   0.00719  -0.0674   0.8016   0.2645
  -5.000  -0.2444   0.01373   0.00667  -0.0615   0.7959   0.3695
  -4.750  -0.2339   0.01421   0.00854  -0.0560   0.7919   0.6170
  -4.500  -0.2186   0.01421   0.00840  -0.0541   0.7881   0.6622
  -4.250  -0.1949   0.01460   0.00865  -0.0531   0.7850   0.6824
  -4.000  -0.1707   0.01517   0.00912  -0.0520   0.7812   0.6975
  -3.750  -0.1407   0.01612   0.00997  -0.0513   0.7781   0.7109
  -3.500  -0.1045   0.01748   0.01126  -0.0511   0.7754   0.7236
  -3.250  -0.0804   0.01778   0.01143  -0.0503   0.7727   0.7337
  -3.000  -0.0531   0.01789   0.01146  -0.0501   0.7695   0.7353
  -2.750  -0.0276   0.01790   0.01139  -0.0499   0.7663   0.7369
  -2.500  -0.0025   0.01784   0.01124  -0.0496   0.7632   0.7391
  -2.250   0.0209   0.01766   0.01096  -0.0493   0.7603   0.7422
  -2.000   0.0400   0.01719   0.01036  -0.0488   0.7577   0.7475
  -1.750   0.0637   0.01718   0.01032  -0.0482   0.7542   0.7486
  -1.500   0.0888   0.01715   0.01025  -0.0479   0.7511   0.7498
  -1.250   0.1146   0.01709   0.01013  -0.0479   0.7482   0.7511
  -1.000   0.1412   0.01700   0.00997  -0.0480   0.7456   0.7526
  -0.750   0.1680   0.01689   0.00980  -0.0483   0.7435   0.7544
  -0.500   0.1889   0.01675   0.00966  -0.0476   0.7398   0.7565
  -0.250   0.2113   0.01653   0.00939  -0.0473   0.7364   0.7595
   0.000   0.2364   0.01632   0.00912  -0.0475   0.7335   0.7615
   0.250   0.2642   0.01626   0.00903  -0.0479   0.7311   0.7623
   0.500   0.2910   0.01624   0.00900  -0.0480   0.7284   0.7632
   0.750   0.3136   0.01625   0.00904  -0.0473   0.7246   0.7643
   1.000   0.3388   0.01620   0.00900  -0.0472   0.7210   0.7654
   1.250   0.3661   0.01613   0.00891  -0.0475   0.7180   0.7664
   1.500   0.3952   0.01605   0.00881  -0.0481   0.7154   0.7674
   1.750   0.4165   0.01604   0.00884  -0.0473   0.7107   0.7689
   2.000   0.4416   0.01598   0.00880  -0.0473   0.7065   0.7705
   2.250   0.4700   0.01587   0.00868  -0.0478   0.7030   0.7719
   2.500   0.4961   0.01579   0.00862  -0.0480   0.6989   0.7732
   2.750   0.5197   0.01572   0.00858  -0.0478   0.6936   0.7747
   3.000   0.5479   0.01561   0.00848  -0.0482   0.6891   0.7757
   3.250   0.5728   0.01559   0.00852  -0.0479   0.6840   0.7764
   3.500   0.5960   0.01557   0.00856  -0.0473   0.6778   0.7773
   3.750   0.6250   0.01549   0.00850  -0.0477   0.6731   0.7783
   4.000   0.6451   0.01550   0.00861  -0.0465   0.6658   0.7794
   4.250   0.6723   0.01542   0.00857  -0.0466   0.6598   0.7803
   4.500   0.6936   0.01540   0.00865  -0.0456   0.6519   0.7814
   4.750   0.7207   0.01531   0.00857  -0.0457   0.6447   0.7824
   5.000   0.7405   0.01530   0.00867  -0.0445   0.6351   0.7836
   5.250   0.7634   0.01525   0.00869  -0.0438   0.6254   0.7848
   5.500   0.7866   0.01519   0.00868  -0.0432   0.6145   0.7861
   5.750   0.8081   0.01515   0.00869  -0.0423   0.6018   0.7875
   6.000   0.8273   0.01514   0.00873  -0.0409   0.5863   0.7892
   6.250   0.8442   0.01516   0.00880  -0.0390   0.5669   0.7903
   6.500   0.8604   0.01520   0.00886  -0.0369   0.5431   0.7913
   6.750   0.8722   0.01530   0.00890  -0.0339   0.5129   0.7923
   7.000   0.8799   0.01556   0.00902  -0.0303   0.4780   0.7936
   7.250   0.8850   0.01603   0.00933  -0.0265   0.4418   0.7949
   7.500   0.8886   0.01668   0.00982  -0.0226   0.4058   0.7964
   7.750   0.8920   0.01741   0.01041  -0.0190   0.3720   0.7980
   8.000   0.8945   0.01825   0.01111  -0.0155   0.3375   0.7996
   8.250   0.8973   0.01917   0.01189  -0.0123   0.3054   0.8014
   8.500   0.9008   0.02017   0.01277  -0.0094   0.2744   0.8033
   8.750   0.9042   0.02117   0.01369  -0.0066   0.2452   0.8047
   9.000   0.9079   0.02225   0.01467  -0.0039   0.2164   0.8060
   9.250   0.9126   0.02337   0.01568  -0.0016   0.1897   0.8073
   9.500   0.9181   0.02452   0.01674   0.0005   0.1642   0.8087
   9.750   0.9255   0.02563   0.01779   0.0022   0.1419   0.8101
  10.250   0.9419   0.02793   0.02000   0.0052   0.1060   0.8131
  10.500   0.9507   0.02911   0.02115   0.0065   0.0907   0.8146
  10.750   0.9590   0.03037   0.02237   0.0078   0.0762   0.8162
  11.000   0.9679   0.03164   0.02366   0.0089   0.0653   0.8177
  11.250   0.9755   0.03293   0.02499   0.0103   0.0564   0.8190
  11.500   0.9827   0.03430   0.02638   0.0115   0.0486   0.8206
  11.750   0.9911   0.03564   0.02779   0.0126   0.0422   0.8222
  12.000   0.9967   0.03725   0.02941   0.0138   0.0368   0.8240
  12.250   1.0055   0.03866   0.03094   0.0147   0.0329   0.8257
  12.500   1.0124   0.04026   0.03260   0.0155   0.0292   0.8274
  12.750   1.0171   0.04212   0.03451   0.0163   0.0260   0.8291
  13.000   1.0255   0.04372   0.03624   0.0169   0.0235   0.8309
  13.250   1.0320   0.04547   0.03807   0.0175   0.0209   0.8325
  13.500   1.0326   0.04781   0.04046   0.0183   0.0186   0.8340
  13.750   1.0392   0.04967   0.04252   0.0187   0.0171   0.8357
  14.000   1.0445   0.05172   0.04470   0.0191   0.0156   0.8375
  14.250   1.0488   0.05393   0.04700   0.0192   0.0139   0.8394
  14.500   1.0463   0.05697   0.05011   0.0194   0.0126   0.8414
  14.750   1.0501   0.05944   0.05276   0.0194   0.0116   0.8434
  15.000   1.0515   0.06228   0.05575   0.0193   0.0109   0.8455
  15.250   1.0519   0.06522   0.05885   0.0191   0.0101   0.8474
  15.500   1.0517   0.06834   0.06211   0.0186   0.0095   0.8496
  15.750   1.0503   0.07171   0.06562   0.0180   0.0092   0.8519
  16.000   1.0463   0.07558   0.06961   0.0171   0.0086   0.8543
  16.250   1.0384   0.08010   0.07426   0.0159   0.0082   0.8565
  16.500   1.0372   0.08389   0.07822   0.0147   0.0079   0.8590
  16.750   1.0355   0.08778   0.08231   0.0133   0.0075   0.8613
  17.000   1.0303   0.09229   0.08700   0.0117   0.0074   0.8636
  17.250   1.0267   0.09675   0.09165   0.0097   0.0068   0.8663
  17.500   1.0211   0.10162   0.09669   0.0075   0.0065   0.8691
  17.750   1.0142   0.10684   0.10207   0.0050   0.0064   0.8719
  18.000   1.0069   0.11227   0.10767   0.0022   0.0061   0.8748
  18.250   0.9984   0.11801   0.11359  -0.0007   0.0060   0.8780
  18.500   0.9906   0.12375   0.11950  -0.0039   0.0058   0.8818
  18.750   0.9812   0.12993   0.12583  -0.0074   0.0057   0.8859
  19.000   0.9702   0.13651   0.13257  -0.0111   0.0057   0.8902
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