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EPPLER 541 AIRFOIL (e541-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 541 AIRFOIL (e541-il)
Reynolds number: 500,000
Max Cl/Cd: 78.33 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e541-il-500000.txt
Download as CSV file: xf-e541-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 541 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.000  -0.2559   0.14424   0.14214  -0.0566   0.9905   0.0157
 -15.750  -0.2508   0.14114   0.13903  -0.0597   0.9827   0.0158
  -8.500  -0.4805   0.02629   0.02024  -0.0812   0.8356   0.0112
  -8.250  -0.4326   0.02285   0.01658  -0.0852   0.8342   0.0098
  -8.000  -0.3846   0.02049   0.01394  -0.0884   0.8330   0.0091
  -7.750  -0.3489   0.01909   0.01236  -0.0895   0.8311   0.0089
  -7.500  -0.3237   0.01825   0.01139  -0.0892   0.8287   0.0088
  -7.250  -0.3036   0.01749   0.01056  -0.0881   0.8260   0.0089
  -7.000  -0.2859   0.01682   0.00985  -0.0867   0.8230   0.0094
  -6.750  -0.2687   0.01626   0.00924  -0.0852   0.8201   0.0097
  -6.500  -0.2520   0.01570   0.00860  -0.0836   0.8172   0.0103
  -6.250  -0.2380   0.01502   0.00783  -0.0815   0.8146   0.0119
  -6.000  -0.2212   0.01459   0.00737  -0.0800   0.8121   0.0138
  -5.750  -0.2073   0.01402   0.00680  -0.0778   0.8093   0.0227
  -5.500  -0.1985   0.01330   0.00634  -0.0750   0.8065   0.0672
  -5.250  -0.1878   0.01271   0.00597  -0.0725   0.8039   0.1163
  -5.000  -0.1871   0.01188   0.00553  -0.0683   0.8013   0.2037
  -4.750  -0.2023   0.01109   0.00517  -0.0611   0.7980   0.3022
  -4.500  -0.2151   0.01014   0.00473  -0.0543   0.7946   0.4217
  -4.250  -0.2316   0.00870   0.00433  -0.0466   0.7915   0.6366
  -4.000  -0.2055   0.00935   0.00516  -0.0456   0.7897   0.7272
  -3.750  -0.1760   0.00989   0.00561  -0.0456   0.7881   0.7425
  -3.500  -0.1455   0.01054   0.00619  -0.0457   0.7865   0.7537
  -3.250  -0.1142   0.01123   0.00683  -0.0459   0.7849   0.7608
  -3.000  -0.0850   0.01180   0.00739  -0.0457   0.7832   0.7669
  -2.750  -0.0466   0.01305   0.00865  -0.0464   0.7817   0.7710
  -2.500  -0.0116   0.01419   0.00976  -0.0465   0.7799   0.7803
  -2.250   0.0363   0.01537   0.01093  -0.0488   0.7786   0.7818
  -2.000   0.0677   0.01553   0.01105  -0.0495   0.7769   0.7831
  -1.750   0.0735   0.01498   0.01042  -0.0468   0.7746   0.7929
  -1.500   0.1036   0.01499   0.01038  -0.0473   0.7731   0.7935
  -1.250   0.1338   0.01503   0.01037  -0.0479   0.7716   0.7941
  -1.000   0.1606   0.01506   0.01040  -0.0479   0.7697   0.7949
  -0.750   0.1869   0.01507   0.01041  -0.0478   0.7675   0.7958
  -0.500   0.2132   0.01506   0.01039  -0.0478   0.7652   0.7969
  -0.250   0.2393   0.01501   0.01033  -0.0477   0.7631   0.7983
   0.000   0.2651   0.01492   0.01022  -0.0477   0.7610   0.8000
   0.250   0.2891   0.01471   0.00997  -0.0477   0.7589   0.8025
   0.500   0.3062   0.01420   0.00939  -0.0471   0.7563   0.8074
   0.750   0.3303   0.01413   0.00937  -0.0465   0.7530   0.8081
   1.000   0.3563   0.01405   0.00930  -0.0464   0.7498   0.8088
   1.250   0.3838   0.01392   0.00915  -0.0466   0.7468   0.8094
   1.500   0.4133   0.01380   0.00900  -0.0473   0.7440   0.8101
   1.750   0.4374   0.01375   0.00898  -0.0469   0.7405   0.8111
   2.000   0.4617   0.01363   0.00889  -0.0465   0.7366   0.8122
   2.250   0.4884   0.01345   0.00871  -0.0468   0.7332   0.8131
   2.500   0.5179   0.01328   0.00852  -0.0475   0.7300   0.8141
   2.750   0.5415   0.01315   0.00842  -0.0472   0.7257   0.8157
   3.000   0.5666   0.01294   0.00823  -0.0472   0.7211   0.8169
   3.250   0.5958   0.01272   0.00800  -0.0480   0.7172   0.8180
   3.500   0.6228   0.01253   0.00783  -0.0485   0.7127   0.8191
   3.750   0.6490   0.01233   0.00766  -0.0489   0.7070   0.8207
   4.000   0.6773   0.01213   0.00745  -0.0492   0.7021   0.8213
   4.250   0.7002   0.01198   0.00738  -0.0485   0.6959   0.8218
   4.500   0.7262   0.01181   0.00724  -0.0484   0.6896   0.8224
   4.750   0.7502   0.01167   0.00716  -0.0479   0.6825   0.8230
   5.000   0.7749   0.01152   0.00704  -0.0475   0.6745   0.8235
   5.250   0.7966   0.01140   0.00700  -0.0466   0.6643   0.8242
   5.500   0.8187   0.01129   0.00693  -0.0456   0.6524   0.8250
   5.750   0.8395   0.01121   0.00688  -0.0445   0.6377   0.8259
   6.000   0.8585   0.01115   0.00681  -0.0429   0.6177   0.8269
   6.250   0.8742   0.01116   0.00677  -0.0408   0.5894   0.8278
   6.500   0.8837   0.01132   0.00681  -0.0375   0.5512   0.8289
   6.750   0.8822   0.01163   0.00692  -0.0321   0.5085   0.8302
   7.000   0.8786   0.01214   0.00722  -0.0266   0.4648   0.8316
   7.250   0.8758   0.01289   0.00774  -0.0216   0.4198   0.8330
   7.500   0.8764   0.01369   0.00834  -0.0175   0.3786   0.8342
   7.750   0.8779   0.01445   0.00895  -0.0137   0.3413   0.8354
   8.000   0.8809   0.01524   0.00960  -0.0103   0.3067   0.8364
   8.250   0.8847   0.01611   0.01031  -0.0071   0.2718   0.8373
   8.500   0.8904   0.01698   0.01104  -0.0045   0.2393   0.8382
   8.750   0.8976   0.01784   0.01179  -0.0021   0.2098   0.8391
   9.000   0.9061   0.01870   0.01255   0.0000   0.1827   0.8400
   9.250   0.9152   0.01958   0.01332   0.0019   0.1569   0.8409
   9.500   0.9245   0.02049   0.01413   0.0037   0.1338   0.8419
   9.750   0.9339   0.02143   0.01496   0.0054   0.1115   0.8428
  10.000   0.9440   0.02237   0.01581   0.0069   0.0911   0.8438
  10.250   0.9533   0.02338   0.01673   0.0085   0.0731   0.8448
  10.500   0.9628   0.02443   0.01770   0.0100   0.0575   0.8460
  10.750   0.9725   0.02550   0.01872   0.0114   0.0451   0.8470
  11.000   0.9819   0.02663   0.01979   0.0128   0.0357   0.8478
  11.250   0.9944   0.02758   0.02078   0.0138   0.0309   0.8485
  11.500   1.0019   0.02882   0.02204   0.0153   0.0263   0.8494
  11.750   1.0156   0.02965   0.02295   0.0161   0.0237   0.8502
  12.000   1.0252   0.03080   0.02412   0.0173   0.0207   0.8511
  12.250   1.0318   0.03222   0.02561   0.0187   0.0180   0.8520
  12.500   1.0440   0.03325   0.02672   0.0195   0.0158   0.8529
  12.750   1.0476   0.03498   0.02845   0.0209   0.0124   0.8538
  13.000   1.0594   0.03612   0.02968   0.0216   0.0108   0.8548
  13.250   1.0664   0.03768   0.03127   0.0225   0.0090   0.8558
  13.500   1.0620   0.04028   0.03399   0.0242   0.0080   0.8568
  13.750   1.0702   0.04187   0.03569   0.0248   0.0075   0.8578
  14.000   1.0782   0.04351   0.03743   0.0254   0.0066   0.8589
  14.250   1.0839   0.04540   0.03940   0.0259   0.0061   0.8600
  14.500   1.0865   0.04766   0.04175   0.0265   0.0057   0.8612
  14.750   1.0857   0.05035   0.04453   0.0270   0.0054   0.8621
  15.000   1.0753   0.05415   0.04849   0.0278   0.0051   0.8629
  15.250   1.0730   0.05719   0.05167   0.0281   0.0050   0.8638
  15.500   1.0768   0.05964   0.05425   0.0280   0.0048   0.8648
  15.750   1.0758   0.06276   0.05752   0.0279   0.0047   0.8657
  16.000   1.0744   0.06602   0.06093   0.0276   0.0046   0.8667
  16.250   1.0719   0.06954   0.06460   0.0271   0.0045   0.8676
  16.500   1.0687   0.07330   0.06851   0.0264   0.0045   0.8686
  16.750   1.0647   0.07731   0.07268   0.0253   0.0043   0.8695
  17.000   1.0581   0.08183   0.07738   0.0240   0.0043   0.8704
  17.250   1.0527   0.08632   0.08202   0.0224   0.0043   0.8713
  17.500   1.0447   0.09143   0.08729   0.0204   0.0042   0.8722
  17.750   1.0351   0.09696   0.09300   0.0181   0.0042   0.8731
  18.000   1.0253   0.10268   0.09889   0.0154   0.0042   0.8739
  18.250   1.0125   0.10917   0.10557   0.0122   0.0042   0.8746
  18.500   1.0007   0.11569   0.11225   0.0087   0.0043   0.8753
  18.750   0.9871   0.12276   0.11948   0.0047   0.0043   0.8760
  19.000   0.9710   0.13056   0.12746   0.0002   0.0043   0.8766
  19.250   0.9559   0.13837   0.13543  -0.0044   0.0043   0.8774
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