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EPPLER 540 AIRFOIL (e540-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 540 AIRFOIL (e540-il)
Reynolds number: 100,000
Max Cl/Cd: 33.41 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e540-il-100000-n5.txt
Download as CSV file: xf-e540-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.4603   0.09250   0.08743  -0.0708   1.0000   0.0150
 -12.250  -0.4745   0.08706   0.08200  -0.0730   1.0000   0.0147
 -12.000  -0.4987   0.08092   0.07579  -0.0752   1.0000   0.0147
 -11.750  -0.5148   0.07710   0.07197  -0.0755   1.0000   0.0144
 -11.500  -0.5359   0.07344   0.06829  -0.0748   1.0000   0.0141
 -11.250  -0.5641   0.07010   0.06489  -0.0726   1.0000   0.0142
 -11.000  -0.5880   0.06741   0.06213  -0.0702   0.9986   0.0141
 -10.750  -0.5971   0.06234   0.05678  -0.0726   0.9894   0.0141
 -10.500  -0.6045   0.05806   0.05220  -0.0737   0.9791   0.0141
 -10.250  -0.6092   0.05418   0.04796  -0.0741   0.9688   0.0142
 -10.000  -0.6109   0.05071   0.04407  -0.0739   0.9588   0.0146
  -9.750  -0.6098   0.04789   0.04080  -0.0728   0.9489   0.0149
  -9.250  -0.5884   0.04202   0.03433  -0.0725   0.9350   0.0160
  -9.000  -0.5670   0.03967   0.03167  -0.0734   0.9303   0.0169
  -8.750  -0.5454   0.03741   0.02909  -0.0734   0.9241   0.0173
  -8.500  -0.5149   0.03499   0.02634  -0.0745   0.9199   0.0180
  -8.250  -0.4734   0.03260   0.02366  -0.0769   0.9181   0.0191
  -8.000  -0.4314   0.03075   0.02158  -0.0792   0.9164   0.0203
  -7.750  -0.3967   0.02934   0.02001  -0.0804   0.9131   0.0224
  -7.500  -0.3738   0.02821   0.01885  -0.0803   0.9068   0.0255
  -7.250  -0.3456   0.02710   0.01761  -0.0809   0.9024   0.0295
  -7.000  -0.3264   0.02606   0.01650  -0.0801   0.8960   0.0330
  -6.500  -0.2832   0.02420   0.01467  -0.0794   0.8855   0.0595
  -6.250  -0.2706   0.02346   0.01418  -0.0772   0.8783   0.0969
  -6.000  -0.2560   0.02239   0.01369  -0.0758   0.8734   0.1945
  -5.750  -0.2109   0.02436   0.01785  -0.0730   0.8726   0.5730
  -5.500  -0.2112   0.02451   0.01790  -0.0684   0.8640   0.6201
  -5.250  -0.2060   0.02461   0.01783  -0.0648   0.8581   0.6531
  -5.000  -0.2101   0.02503   0.01815  -0.0590   0.8500   0.6733
  -4.750  -0.1936   0.02563   0.01856  -0.0566   0.8455   0.6926
  -4.500  -0.1432   0.02721   0.01990  -0.0583   0.8440   0.7107
  -4.250  -0.0986   0.02850   0.02097  -0.0594   0.8412   0.7278
  -4.000  -0.0720   0.02888   0.02121  -0.0588   0.8365   0.7371
  -3.750  -0.0701   0.02876   0.02097  -0.0547   0.8313   0.7473
  -3.500  -0.0282   0.02864   0.02066  -0.0574   0.8294   0.7495
  -3.250  -0.0061   0.02869   0.02060  -0.0566   0.8245   0.7534
  -3.000  -0.0107   0.02854   0.02037  -0.0514   0.8185   0.7620
  -2.750   0.0242   0.02837   0.02006  -0.0530   0.8161   0.7640
  -2.500   0.0474   0.02832   0.01992  -0.0525   0.8124   0.7672
  -2.250   0.0318   0.02822   0.01979  -0.0455   0.8054   0.7756
  -2.000   0.0640   0.02805   0.01950  -0.0466   0.8028   0.7772
  -1.750   0.0960   0.02785   0.01920  -0.0478   0.8007   0.7791
  -1.500   0.0983   0.02802   0.01936  -0.0436   0.7944   0.7832
  -1.250   0.0931   0.02773   0.01902  -0.0386   0.7893   0.7897
  -1.000   0.1250   0.02756   0.01876  -0.0397   0.7872   0.7911
  -0.750   0.1339   0.02772   0.01892  -0.0367   0.7816   0.7936
  -0.500   0.1477   0.02768   0.01885  -0.0346   0.7771   0.7964
  -0.250   0.1665   0.02746   0.01857  -0.0336   0.7741   0.7994
   0.000   0.1572   0.02741   0.01851  -0.0278   0.7678   0.8042
   0.250   0.1732   0.02743   0.01851  -0.0261   0.7631   0.8058
   0.500   0.1990   0.02727   0.01832  -0.0262   0.7603   0.8072
   0.750   0.2294   0.02706   0.01808  -0.0272   0.7583   0.8088
   1.000   0.2158   0.02735   0.01841  -0.0205   0.7496   0.8124
   1.250   0.2384   0.02713   0.01815  -0.0202   0.7463   0.8143
   1.500   0.2664   0.02683   0.01782  -0.0209   0.7441   0.8165
   2.000   0.2858   0.02698   0.01802  -0.0157   0.7321   0.8199
   2.250   0.3202   0.02673   0.01778  -0.0173   0.7300   0.8208
   2.500   0.3121   0.02715   0.01825  -0.0116   0.7206   0.8236
   2.750   0.3435   0.02692   0.01804  -0.0127   0.7177   0.8249
   3.250   0.3716   0.02699   0.01817  -0.0092   0.7054   0.8284
   3.500   0.4087   0.02667   0.01790  -0.0112   0.7028   0.8293
   4.000   0.4414   0.02667   0.01801  -0.0083   0.6898   0.8328
   4.250   0.4841   0.02623   0.01765  -0.0110   0.6874   0.8334
   4.500   0.4795   0.02660   0.01810  -0.0060   0.6766   0.8354
   4.750   0.5218   0.02608   0.01766  -0.0085   0.6738   0.8360
   5.250   0.5652   0.02580   0.01757  -0.0069   0.6597   0.8386
   5.750   0.6144   0.02533   0.01729  -0.0062   0.6449   0.8416
   6.000   0.6205   0.02563   0.01769  -0.0033   0.6332   0.8440
   6.250   0.6352   0.02575   0.01794  -0.0018   0.6223   0.8458
   6.500   0.6713   0.02505   0.01735  -0.0027   0.6152   0.8466
   6.750   0.6858   0.02507   0.01749  -0.0008   0.6031   0.8480
   7.000   0.6991   0.02517   0.01772   0.0012   0.5894   0.8496
   7.250   0.7154   0.02519   0.01785   0.0027   0.5751   0.8512
   7.500   0.7322   0.02523   0.01803   0.0041   0.5588   0.8529
   7.750   0.7453   0.02550   0.01841   0.0058   0.5390   0.8550
   8.000   0.7729   0.02507   0.01803   0.0060   0.5175   0.8568
   8.250   0.7967   0.02491   0.01788   0.0066   0.4900   0.8587
   8.500   0.8190   0.02484   0.01775   0.0075   0.4566   0.8603
   8.750   0.8366   0.02504   0.01783   0.0089   0.4197   0.8618
   9.000   0.8480   0.02564   0.01835   0.0108   0.3833   0.8636
   9.250   0.8562   0.02650   0.01906   0.0128   0.3476   0.8655
   9.500   0.8626   0.02753   0.01998   0.0148   0.3133   0.8676
   9.750   0.8682   0.02871   0.02103   0.0166   0.2799   0.8698
  10.000   0.8739   0.02999   0.02219   0.0182   0.2489   0.8721
  10.250   0.8786   0.03135   0.02344   0.0198   0.2193   0.8744
  10.500   0.8829   0.03271   0.02472   0.0216   0.1919   0.8767
  10.750   0.8884   0.03411   0.02606   0.0230   0.1670   0.8793
  11.000   0.8936   0.03563   0.02750   0.0242   0.1430   0.8820
  11.250   0.8991   0.03723   0.02904   0.0253   0.1233   0.8846
  11.500   0.9060   0.03884   0.03067   0.0261   0.1051   0.8871
  11.750   0.9114   0.04047   0.03232   0.0271   0.0909   0.8894
  12.000   0.9162   0.04222   0.03408   0.0281   0.0797   0.8920
  12.250   0.9197   0.04414   0.03600   0.0290   0.0701   0.8949
  12.500   0.9255   0.04600   0.03794   0.0296   0.0614   0.8979
  12.750   0.9301   0.04804   0.04006   0.0302   0.0551   0.9010
  13.000   0.9338   0.05006   0.04219   0.0309   0.0501   0.9043
  13.250   0.9357   0.05230   0.04449   0.0316   0.0461   0.9082
  13.500   0.9415   0.05434   0.04671   0.0320   0.0413   0.9126
  13.750   0.9435   0.05674   0.04920   0.0323   0.0380   0.9173
  14.000   0.9462   0.05916   0.05172   0.0327   0.0353   0.9225
  14.250   0.9513   0.06149   0.05428   0.0327   0.0320   0.9289
  14.500   0.9539   0.06416   0.05710   0.0323   0.0293   0.9368
  14.750   0.9545   0.06722   0.06029   0.0317   0.0273   0.9467
  15.000   0.9570   0.06988   0.06315   0.0314   0.0256   0.9696
  15.250   0.9587   0.07296   0.06647   0.0306   0.0236   1.0000
  15.500   0.9591   0.07652   0.07019   0.0293   0.0218   1.0000
  15.750   0.9585   0.08025   0.07405   0.0278   0.0206   1.0000
  16.000   0.9566   0.08423   0.07814   0.0263   0.0197   1.0000
  16.500   0.9488   0.09322   0.08748   0.0230   0.0182   1.0000
  16.750   0.9421   0.09843   0.09294   0.0207   0.0177   1.0000
  17.000   0.9331   0.10419   0.09894   0.0178   0.0173   1.0000
  17.250   0.9209   0.11075   0.10574   0.0142   0.0168   1.0000
  17.500   0.9077   0.11773   0.11293   0.0101   0.0164   1.0000
  17.750   0.8926   0.12542   0.12082   0.0056   0.0164   1.0000
  18.000   0.8744   0.13421   0.12981   0.0002   0.0165   1.0000
  18.250   0.8523   0.14455   0.14031  -0.0062   0.0168   1.0000
  18.500   0.8295   0.15573   0.15161  -0.0129   0.0176   1.0000
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