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EPPLER 557 AIRFOIL (e557-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 557 AIRFOIL (e557-il)
Reynolds number: 100,000
Max Cl/Cd: 53.73 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e557-il-100000.txt
Download as CSV file: xf-e557-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 557 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.5304   0.08136   0.07627  -0.0715   1.0000   0.0534
 -11.000  -0.5397   0.07719   0.07213  -0.0717   1.0000   0.0526
 -10.750  -0.5637   0.07257   0.06750  -0.0725   1.0000   0.0521
 -10.500  -0.5898   0.06873   0.06364  -0.0725   1.0000   0.0516
 -10.250  -0.6152   0.06554   0.06043  -0.0714   1.0000   0.0507
 -10.000  -0.6472   0.06317   0.05804  -0.0690   1.0000   0.0502
  -9.750  -0.6788   0.06100   0.05585  -0.0664   1.0000   0.0497
  -9.500  -0.7042   0.05788   0.05256  -0.0653   1.0000   0.0489
  -9.250  -0.7218   0.05466   0.04912  -0.0642   1.0000   0.0486
  -9.000  -0.7332   0.05099   0.04509  -0.0636   1.0000   0.0478
  -8.750  -0.7317   0.04857   0.04246  -0.0628   1.0000   0.0490
  -8.500  -0.7273   0.04585   0.03943  -0.0625   1.0000   0.0502
  -8.250  -0.7186   0.04301   0.03620  -0.0624   1.0000   0.0512
  -8.000  -0.7056   0.04031   0.03309  -0.0623   1.0000   0.0521
  -7.750  -0.6893   0.03790   0.03024  -0.0621   1.0000   0.0532
  -7.500  -0.6728   0.03546   0.02768  -0.0614   1.0000   0.0550
  -7.250  -0.6560   0.03416   0.02641  -0.0608   1.0000   0.0587
  -7.000  -0.6196   0.03238   0.02438  -0.0632   0.9956   0.0648
  -6.750  -0.5815   0.03105   0.02299  -0.0659   0.9899   0.0734
  -6.500  -0.5435   0.02965   0.02169  -0.0686   0.9845   0.0854
  -6.250  -0.5099   0.02820   0.02044  -0.0705   0.9780   0.1020
  -6.000  -0.4684   0.02664   0.01918  -0.0746   0.9729   0.1330
  -5.750  -0.4238   0.02320   0.01724  -0.0823   0.9676   0.3045
  -5.500  -0.3828   0.02540   0.01947  -0.0834   0.9597   0.4139
  -5.250  -0.3510   0.02698   0.02093  -0.0830   0.9503   0.4424
  -5.000  -0.3227   0.02852   0.02247  -0.0815   0.9413   0.4603
  -4.750  -0.2880   0.02997   0.02386  -0.0810   0.9341   0.4772
  -4.500  -0.2618   0.03074   0.02453  -0.0801   0.9245   0.4919
  -4.250  -0.2260   0.03182   0.02558  -0.0797   0.9185   0.5050
  -4.000  -0.2076   0.03260   0.02636  -0.0766   0.9080   0.5137
  -3.750  -0.1693   0.03319   0.02685  -0.0771   0.9028   0.5284
  -3.500  -0.1461   0.03331   0.02685  -0.0767   0.8923   0.5421
  -3.250  -0.1127   0.03384   0.02738  -0.0754   0.8871   0.5500
  -3.000  -0.0846   0.03323   0.02660  -0.0773   0.8770   0.5598
  -2.750  -0.0465   0.03304   0.02634  -0.0783   0.8719   0.5653
  -2.500  -0.0139   0.03238   0.02550  -0.0812   0.8625   0.5731
  -2.250   0.0265   0.03180   0.02482  -0.0836   0.8570   0.5781
  -2.000   0.0569   0.03150   0.02444  -0.0844   0.8490   0.5825
  -1.750   0.0999   0.03075   0.02354  -0.0884   0.8424   0.5891
  -1.500   0.1515   0.02983   0.02250  -0.0930   0.8393   0.5938
  -1.250   0.1715   0.02979   0.02243  -0.0920   0.8282   0.5975
  -1.000   0.2219   0.02899   0.02153  -0.0963   0.8246   0.6033
  -0.750   0.2834   0.02791   0.02029  -0.1032   0.8222   0.6090
  -0.500   0.2998   0.02796   0.02036  -0.1013   0.8104   0.6123
  -0.250   0.3520   0.02722   0.01957  -0.1054   0.8070   0.6177
   0.000   0.3829   0.02699   0.01925  -0.1071   0.7969   0.6233
   0.250   0.4291   0.02630   0.01853  -0.1102   0.7919   0.6275
   0.500   0.4581   0.02615   0.01838  -0.1104   0.7830   0.6318
   0.750   0.5009   0.02564   0.01783  -0.1133   0.7762   0.6381
   1.000   0.5395   0.02526   0.01741  -0.1155   0.7687   0.6433
   1.250   0.5707   0.02503   0.01720  -0.1159   0.7600   0.6475
   1.500   0.6056   0.02481   0.01697  -0.1174   0.7517   0.6533
   1.750   0.6422   0.02451   0.01664  -0.1192   0.7431   0.6595
   2.000   0.6683   0.02451   0.01668  -0.1187   0.7336   0.6644
   2.250   0.7075   0.02417   0.01632  -0.1207   0.7257   0.6710
   2.500   0.7332   0.02425   0.01642  -0.1207   0.7151   0.6764
   2.750   0.7719   0.02388   0.01606  -0.1222   0.7080   0.6826
   3.000   0.7957   0.02409   0.01630  -0.1219   0.6965   0.6900
   3.250   0.8308   0.02384   0.01607  -0.1228   0.6888   0.6961
   3.500   0.8554   0.02394   0.01623  -0.1223   0.6778   0.7030
   3.750   0.8820   0.02403   0.01637  -0.1222   0.6676   0.7099
   4.000   0.9168   0.02381   0.01615  -0.1231   0.6590   0.7179
   4.250   0.9383   0.02405   0.01648  -0.1221   0.6474   0.7259
   4.500   0.9682   0.02399   0.01646  -0.1222   0.6380   0.7343
   4.750   0.9974   0.02396   0.01647  -0.1223   0.6274   0.7431
   5.000   1.0191   0.02416   0.01676  -0.1213   0.6159   0.7526
   5.250   1.0497   0.02405   0.01669  -0.1214   0.6062   0.7627
   5.500   1.0759   0.02408   0.01679  -0.1210   0.5947   0.7743
   5.750   1.0967   0.02427   0.01708  -0.1196   0.5829   0.7859
   6.000   1.1231   0.02424   0.01710  -0.1190   0.5721   0.7985
   6.250   1.1500   0.02415   0.01706  -0.1185   0.5609   0.8132
   6.500   1.1672   0.02433   0.01737  -0.1164   0.5484   0.8294
   6.750   1.1875   0.02438   0.01752  -0.1148   0.5366   0.8487
   7.000   1.2108   0.02419   0.01737  -0.1134   0.5255   0.8723
   7.250   1.2220   0.02409   0.01742  -0.1100   0.5134   0.9069
   7.500   1.2460   0.02405   0.01752  -0.1095   0.4993   1.0000
   7.750   1.2813   0.02434   0.01778  -0.1116   0.4833   1.0000
   8.000   1.3108   0.02464   0.01806  -0.1124   0.4674   1.0000
   8.250   1.3359   0.02495   0.01835  -0.1122   0.4512   1.0000
   8.500   1.3580   0.02528   0.01867  -0.1114   0.4348   1.0000
   8.750   1.3776   0.02564   0.01900  -0.1100   0.4179   1.0000
   9.000   1.3950   0.02604   0.01938  -0.1083   0.4006   1.0000
   9.250   1.4105   0.02649   0.01980  -0.1063   0.3830   1.0000
   9.500   1.4226   0.02704   0.02031  -0.1038   0.3649   1.0000
   9.750   1.4290   0.02770   0.02099  -0.1004   0.3470   1.0000
  10.000   1.4332   0.02844   0.02174  -0.0968   0.3291   1.0000
  10.250   1.4367   0.02931   0.02259  -0.0932   0.3113   1.0000
  10.500   1.4393   0.03030   0.02356  -0.0897   0.2937   1.0000
  10.750   1.4413   0.03144   0.02467  -0.0864   0.2765   1.0000
  11.000   1.4427   0.03274   0.02592  -0.0832   0.2599   1.0000
  11.250   1.4437   0.03420   0.02733  -0.0803   0.2438   1.0000
  11.500   1.4444   0.03581   0.02890  -0.0776   0.2285   1.0000
  11.750   1.4448   0.03758   0.03064  -0.0750   0.2138   1.0000
  12.000   1.4452   0.03948   0.03252  -0.0728   0.2000   1.0000
  12.250   1.4459   0.04151   0.03454  -0.0707   0.1870   1.0000
  12.500   1.4472   0.04362   0.03663  -0.0689   0.1750   1.0000
  12.750   1.4502   0.04574   0.03867  -0.0674   0.1635   1.0000
  13.000   1.4494   0.04808   0.04107  -0.0658   0.1532   1.0000
  13.250   1.4494   0.05061   0.04368  -0.0644   0.1434   1.0000
  13.500   1.4532   0.05297   0.04598  -0.0634   0.1341   1.0000
  13.750   1.4520   0.05562   0.04871  -0.0623   0.1259   1.0000
  14.000   1.4529   0.05841   0.05158  -0.0614   0.1182   1.0000
  14.250   1.4571   0.06083   0.05395  -0.0607   0.1107   1.0000
  14.500   1.4542   0.06412   0.05745  -0.0601   0.1045   1.0000
  14.750   1.4584   0.06665   0.05994  -0.0596   0.0981   1.0000
  15.000   1.4570   0.07010   0.06358  -0.0592   0.0930   1.0000
  15.250   1.4543   0.07345   0.06706  -0.0591   0.0881   1.0000
  15.500   1.4637   0.07606   0.06962  -0.0588   0.0828   1.0000
  15.750   1.4526   0.08054   0.07442  -0.0591   0.0797   1.0000
  16.000   1.4506   0.08405   0.07804  -0.0595   0.0760   1.0000
  16.250   1.4593   0.08690   0.08084  -0.0594   0.0717   1.0000
  16.500   1.4435   0.09228   0.08657  -0.0606   0.0700   1.0000
  16.750   1.4302   0.09760   0.09217  -0.0621   0.0680   1.0000
  17.000   1.4198   0.10258   0.09733  -0.0637   0.0659   1.0000
  17.250   1.4363   0.10433   0.09892  -0.0634   0.0619   1.0000
  17.500   1.4130   0.11124   0.10617  -0.0664   0.0613   1.0000
  17.750   1.3886   0.11880   0.11405  -0.0702   0.0609   1.0000
  18.000   1.3619   0.12721   0.12276  -0.0750   0.0607   1.0000
  18.250   1.3325   0.13670   0.13250  -0.0808   0.0609   1.0000
  18.500   1.2994   0.14758   0.14361  -0.0880   0.0614   1.0000
  18.750   1.2642   0.15986   0.15608  -0.0963   0.0621   1.0000
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