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EPPLER 541 AIRFOIL (e541-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 541 AIRFOIL (e541-il)
Reynolds number: 100,000
Max Cl/Cd: 29.34 at α=9°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e541-il-100000-n5.txt
Download as CSV file: xf-e541-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.4101   0.11114   0.10628  -0.0645   1.0000   0.0159
 -12.500  -0.4198   0.10709   0.10233  -0.0649   1.0000   0.0157
 -12.250  -0.4326   0.10253   0.09785  -0.0655   0.9991   0.0155
 -12.000  -0.4358   0.09332   0.08863  -0.0725   0.9915   0.0153
 -11.750  -0.4482   0.08424   0.07946  -0.0799   0.9838   0.0151
 -11.500  -0.4606   0.07758   0.07271  -0.0851   0.9758   0.0148
 -11.250  -0.4749   0.07135   0.06631  -0.0894   0.9694   0.0146
 -11.000  -0.4916   0.06585   0.06057  -0.0917   0.9616   0.0146
 -10.750  -0.5020   0.06096   0.05540  -0.0936   0.9560   0.0145
 -10.500  -0.5110   0.05702   0.05119  -0.0938   0.9481   0.0143
 -10.250  -0.5141   0.05327   0.04711  -0.0941   0.9422   0.0141
 -10.000  -0.5211   0.04988   0.04337  -0.0924   0.9335   0.0142
  -9.750  -0.5205   0.04660   0.03964  -0.0912   0.9277   0.0143
  -9.500  -0.5212   0.04427   0.03698  -0.0886   0.9197   0.0142
  -9.250  -0.5143   0.04166   0.03394  -0.0867   0.9145   0.0147
  -9.000  -0.5058   0.03952   0.03144  -0.0846   0.9086   0.0149
  -8.750  -0.4913   0.03757   0.02903  -0.0831   0.9035   0.0157
  -8.500  -0.4687   0.03517   0.02637  -0.0833   0.9004   0.0171
  -8.250  -0.4436   0.03350   0.02450  -0.0836   0.8971   0.0182
  -8.000  -0.4117   0.03174   0.02253  -0.0846   0.8941   0.0190
  -7.750  -0.3734   0.02998   0.02055  -0.0862   0.8923   0.0206
  -7.500  -0.3412   0.02869   0.01907  -0.0870   0.8899   0.0220
  -7.250  -0.3155   0.02749   0.01780  -0.0870   0.8872   0.0250
  -7.000  -0.2925   0.02662   0.01687  -0.0867   0.8844   0.0297
  -6.750  -0.2800   0.02608   0.01620  -0.0844   0.8790   0.0325
  -6.500  -0.2644   0.02523   0.01536  -0.0827   0.8749   0.0409
  -6.250  -0.2454   0.02440   0.01456  -0.0816   0.8720   0.0579
  -6.000  -0.2303   0.02367   0.01415  -0.0798   0.8686   0.1001
  -5.750  -0.2214   0.02299   0.01406  -0.0770   0.8641   0.1963
  -5.500  -0.2024   0.02286   0.01601  -0.0732   0.8619   0.5458
  -5.000  -0.1537   0.02573   0.01873  -0.0683   0.8566   0.6965
  -4.750  -0.1403   0.02681   0.01967  -0.0649   0.8520   0.7153
  -4.500  -0.1275   0.02761   0.02033  -0.0616   0.8481   0.7328
  -4.250  -0.0959   0.02883   0.02134  -0.0609   0.8459   0.7528
  -4.000  -0.0429   0.02991   0.02220  -0.0640   0.8452   0.7684
  -3.750  -0.0269   0.02998   0.02212  -0.0621   0.8426   0.7789
  -3.500   0.0051   0.03011   0.02211  -0.0630   0.8399   0.7823
  -3.000   0.0321   0.03033   0.02213  -0.0587   0.8323   0.7948
  -2.750   0.0645   0.03020   0.02186  -0.0600   0.8303   0.7979
  -2.500   0.0575   0.03036   0.02197  -0.0541   0.8259   0.8067
  -2.250   0.0808   0.03050   0.02204  -0.0538   0.8222   0.8092
  -2.000   0.1051   0.03049   0.02194  -0.0536   0.8191   0.8123
  -1.750   0.1217   0.03042   0.02180  -0.0521   0.8163   0.8169
  -1.500   0.1327   0.03029   0.02159  -0.0495   0.8140   0.8218
  -1.250   0.1360   0.03078   0.02209  -0.0456   0.8076   0.8252
  -1.000   0.1510   0.03082   0.02207  -0.0437   0.8041   0.8287
  -0.750   0.1440   0.03071   0.02191  -0.0377   0.8005   0.8350
  -0.500   0.1458   0.03119   0.02241  -0.0335   0.7939   0.8378
  -0.250   0.1624   0.03123   0.02241  -0.0320   0.7902   0.8403
   0.000   0.1818   0.03108   0.02222  -0.0309   0.7876   0.8431
   0.500   0.1589   0.03144   0.02256  -0.0175   0.7747   0.8515
   0.750   0.1900   0.03123   0.02232  -0.0186   0.7728   0.8529
   1.250   0.1678   0.03134   0.02242  -0.0055   0.7593   0.8609
   1.500   0.1873   0.03099   0.02204  -0.0044   0.7569   0.8628
   1.750   0.1716   0.03147   0.02255   0.0026   0.7466   0.8656
   2.000   0.2037   0.03121   0.02228   0.0015   0.7446   0.8666
   2.500   0.2157   0.03128   0.02237   0.0079   0.7316   0.8707
   2.750   0.2483   0.03090   0.02200   0.0069   0.7297   0.8718
   3.250   0.2644   0.03080   0.02193   0.0124   0.7163   0.8760
   4.000   0.3279   0.03046   0.02173   0.0146   0.7001   0.8793
   4.250   0.3333   0.03074   0.02206   0.0175   0.6900   0.8812
   4.500   0.3689   0.03022   0.02160   0.0163   0.6876   0.8817
   5.000   0.4091   0.02993   0.02147   0.0180   0.6737   0.8840
   5.250   0.4165   0.03021   0.02182   0.0204   0.6623   0.8856
   5.500   0.4437   0.02982   0.02151   0.0204   0.6567   0.8867
   5.750   0.4626   0.02970   0.02147   0.0214   0.6476   0.8884
   6.250   0.5114   0.02899   0.02099   0.0221   0.6322   0.8906
   6.500   0.5256   0.02908   0.02118   0.0237   0.6200   0.8918
   6.750   0.5430   0.02903   0.02125   0.0249   0.6080   0.8929
   7.000   0.5634   0.02884   0.02118   0.0257   0.5959   0.8940
   7.250   0.5855   0.02860   0.02109   0.0264   0.5831   0.8951
   7.500   0.6080   0.02833   0.02094   0.0271   0.5686   0.8963
   7.750   0.6332   0.02795   0.02066   0.0275   0.5525   0.8976
   8.000   0.6640   0.02722   0.02003   0.0275   0.5343   0.8988
   8.250   0.6923   0.02670   0.01959   0.0277   0.5098   0.9002
   8.500   0.7248   0.02602   0.01887   0.0275   0.4784   0.9013
   8.750   0.7499   0.02588   0.01861   0.0280   0.4403   0.9024
   9.000   0.7682   0.02618   0.01877   0.0290   0.4006   0.9037
   9.250   0.7805   0.02678   0.01924   0.0307   0.3636   0.9050
   9.500   0.7897   0.02760   0.01994   0.0325   0.3272   0.9064
   9.750   0.7975   0.02856   0.02079   0.0342   0.2928   0.9080
  10.000   0.8046   0.02965   0.02179   0.0359   0.2590   0.9097
  10.250   0.8119   0.03080   0.02284   0.0373   0.2274   0.9114
  10.500   0.8189   0.03205   0.02399   0.0386   0.1974   0.9133
  10.750   0.8260   0.03337   0.02521   0.0399   0.1690   0.9154
  11.250   0.8391   0.03616   0.02784   0.0422   0.1214   0.9194
  11.500   0.8465   0.03757   0.02923   0.0433   0.1027   0.9214
  11.750   0.8535   0.03908   0.03074   0.0442   0.0879   0.9233
  12.000   0.8601   0.04071   0.03239   0.0451   0.0755   0.9253
  12.250   0.8664   0.04242   0.03413   0.0459   0.0654   0.9274
  12.500   0.8708   0.04434   0.03609   0.0466   0.0578   0.9295
  13.000   0.8799   0.04831   0.04021   0.0479   0.0472   0.9339
  13.250   0.8880   0.05010   0.04221   0.0484   0.0425   0.9363
  13.500   0.8926   0.05222   0.04443   0.0487   0.0383   0.9391
  13.750   0.8961   0.05457   0.04685   0.0490   0.0353   0.9420
  14.000   0.9033   0.05668   0.04918   0.0492   0.0320   0.9452
  14.250   0.9073   0.05907   0.05171   0.0490   0.0291   0.9489
  14.500   0.9083   0.06192   0.05462   0.0488   0.0269   0.9528
  14.750   0.9142   0.06452   0.05745   0.0485   0.0249   0.9571
  15.000   0.9176   0.06747   0.06065   0.0477   0.0225   0.9617
  15.250   0.9189   0.07072   0.06406   0.0465   0.0208   0.9673
  15.500   0.9189   0.07404   0.06753   0.0452   0.0198   0.9761
  15.750   0.9155   0.07755   0.07116   0.0444   0.0189   1.0000
  16.000   0.9132   0.08168   0.07554   0.0433   0.0181   1.0000
  16.250   0.9082   0.08637   0.08052   0.0414   0.0173   1.0000
  16.500   0.9011   0.09147   0.08588   0.0392   0.0168   1.0000
  16.750   0.8921   0.09706   0.09171   0.0365   0.0163   1.0000
  17.000   0.8801   0.10338   0.09827   0.0330   0.0157   1.0000
  17.250   0.8679   0.11002   0.10513   0.0292   0.0156   1.0000
  17.500   0.8518   0.11782   0.11314   0.0247   0.0157   1.0000
  17.750   0.8336   0.12646   0.12199   0.0194   0.0158   1.0000
  18.000   0.8117   0.13656   0.13222   0.0131   0.0164   1.0000
  18.250   0.7849   0.14882   0.14463   0.0058   0.0169   1.0000
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