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EPPLER 558 AIRFOIL (e558-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 558 AIRFOIL (e558-il)
Reynolds number: 100,000
Max Cl/Cd: 50.88 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e558-il-100000-n5.txt
Download as CSV file: xf-e558-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 558 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
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -0.5121   0.11194   0.10623  -0.0464   1.0000   0.0289
 -14.000  -0.5503   0.09975   0.09387  -0.0524   1.0000   0.0281
 -13.750  -0.5754   0.09114   0.08510  -0.0568   1.0000   0.0282
 -13.500  -0.5938   0.08433   0.07815  -0.0603   1.0000   0.0285
 -13.250  -0.6064   0.07896   0.07265  -0.0628   1.0000   0.0288
 -13.000  -0.6169   0.07430   0.06786  -0.0647   1.0000   0.0291
 -12.750  -0.6252   0.07015   0.06358  -0.0663   1.0000   0.0294
 -12.500  -0.6312   0.06657   0.05992  -0.0673   1.0000   0.0299
 -12.250  -0.6330   0.06383   0.05720  -0.0677   1.0000   0.0305
 -12.000  -0.6363   0.06095   0.05431  -0.0682   1.0000   0.0310
 -11.750  -0.6415   0.05794   0.05126  -0.0686   1.0000   0.0318
 -11.500  -0.6463   0.05512   0.04841  -0.0688   1.0000   0.0324
 -11.250  -0.6526   0.05230   0.04553  -0.0687   1.0000   0.0332
 -11.000  -0.6593   0.04964   0.04282  -0.0684   1.0000   0.0338
 -10.750  -0.6679   0.04701   0.04014  -0.0679   1.0000   0.0343
 -10.500  -0.6810   0.04433   0.03744  -0.0669   1.0000   0.0349
 -10.250  -0.7008   0.04169   0.03480  -0.0654   1.0000   0.0351
 -10.000  -0.7179   0.03888   0.03196  -0.0648   1.0000   0.0354
  -9.750  -0.7262   0.03668   0.02971  -0.0638   1.0000   0.0361
  -9.500  -0.7293   0.03486   0.02784  -0.0624   1.0000   0.0374
  -9.250  -0.7213   0.03312   0.02597  -0.0624   0.9984   0.0400
  -9.000  -0.6896   0.03092   0.02370  -0.0670   0.9906   0.0448
  -8.750  -0.6572   0.02891   0.02158  -0.0711   0.9830   0.0527
  -8.500  -0.6273   0.02710   0.01971  -0.0741   0.9739   0.0632
  -8.250  -0.5974   0.02542   0.01805  -0.0769   0.9645   0.0796
  -8.000  -0.5651   0.02403   0.01669  -0.0796   0.9560   0.1015
  -7.750  -0.5324   0.02294   0.01562  -0.0819   0.9468   0.1260
  -7.500  -0.5008   0.02213   0.01478  -0.0835   0.9367   0.1503
  -7.250  -0.4633   0.02148   0.01413  -0.0861   0.9296   0.1740
  -7.000  -0.4317   0.02099   0.01354  -0.0872   0.9187   0.1936
  -6.750  -0.3961   0.02056   0.01300  -0.0890   0.9103   0.2117
  -6.500  -0.3605   0.02018   0.01252  -0.0906   0.9010   0.2278
  -6.250  -0.3253   0.01987   0.01212  -0.0920   0.8911   0.2418
  -6.000  -0.2867   0.01956   0.01174  -0.0941   0.8823   0.2549
  -5.750  -0.2524   0.01929   0.01135  -0.0952   0.8706   0.2667
  -5.500  -0.2133   0.01896   0.01086  -0.0973   0.8611   0.2794
  -5.250  -0.1785   0.01873   0.01053  -0.0985   0.8485   0.2903
  -5.000  -0.1440   0.01851   0.01021  -0.0996   0.8357   0.3004
  -4.750  -0.1079   0.01826   0.00975  -0.1011   0.8234   0.3118
  -4.500  -0.0732   0.01809   0.00953  -0.1022   0.8104   0.3206
  -4.250  -0.0418   0.01791   0.00919  -0.1027   0.7959   0.3306
  -4.000  -0.0107   0.01779   0.00899  -0.1031   0.7818   0.3390
  -3.750   0.0208   0.01764   0.00868  -0.1037   0.7684   0.3485
  -3.250   0.0808   0.01743   0.00824  -0.1042   0.7413   0.3657
  -3.000   0.1093   0.01737   0.00812  -0.1041   0.7280   0.3734
  -2.750   0.1387   0.01729   0.00787  -0.1043   0.7156   0.3828
  -2.500   0.1670   0.01723   0.00777  -0.1041   0.7031   0.3901
  -2.250   0.1944   0.01719   0.00761  -0.1040   0.6904   0.3994
  -2.000   0.2222   0.01715   0.00752  -0.1037   0.6788   0.4068
  -1.750   0.2502   0.01712   0.00739  -0.1036   0.6673   0.4161
  -1.500   0.2768   0.01710   0.00733  -0.1033   0.6555   0.4240
  -1.250   0.3045   0.01710   0.00724  -0.1031   0.6451   0.4331
  -1.000   0.3313   0.01710   0.00720  -0.1027   0.6339   0.4417
  -0.750   0.3581   0.01711   0.00716  -0.1024   0.6234   0.4510
  -0.500   0.3854   0.01713   0.00712  -0.1022   0.6137   0.4601
  -0.250   0.4117   0.01716   0.00714  -0.1018   0.6032   0.4699
   0.000   0.4390   0.01720   0.00711  -0.1015   0.5945   0.4795
   0.250   0.4650   0.01725   0.00716  -0.1011   0.5841   0.4901
   0.500   0.4920   0.01730   0.00718  -0.1008   0.5759   0.5002
   0.750   0.5180   0.01738   0.00726  -0.1004   0.5662   0.5118
   1.000   0.5446   0.01744   0.00730  -0.1000   0.5583   0.5231
   1.250   0.5701   0.01752   0.00744  -0.0995   0.5491   0.5351
   1.500   0.5970   0.01762   0.00749  -0.0992   0.5418   0.5488
   1.750   0.6221   0.01772   0.00766  -0.0986   0.5330   0.5626
   2.000   0.6482   0.01781   0.00776  -0.0982   0.5256   0.5776
   2.250   0.6739   0.01793   0.00795  -0.0977   0.5178   0.5942
   2.500   0.6996   0.01805   0.00811  -0.0972   0.5105   0.6126
   2.750   0.7255   0.01818   0.00827  -0.0967   0.5037   0.6337
   3.000   0.7500   0.01830   0.00851  -0.0960   0.4960   0.6577
   3.250   0.7752   0.01841   0.00866  -0.0953   0.4900   0.6851
   3.500   0.7984   0.01853   0.00895  -0.0943   0.4830   0.7180
   3.750   0.8208   0.01862   0.00917  -0.0930   0.4764   0.7591
   4.000   0.8428   0.01867   0.00931  -0.0915   0.4711   0.8131
   4.250   0.8664   0.01868   0.00957  -0.0903   0.4640   0.9077
   4.500   0.8973   0.01890   0.00975  -0.0911   0.4577   1.0000
   4.750   0.9241   0.01922   0.01000  -0.0911   0.4521   1.0000
   5.000   0.9489   0.01957   0.01038  -0.0907   0.4453   1.0000
   5.250   0.9751   0.01989   0.01065  -0.0905   0.4397   1.0000
   5.500   1.0008   0.02025   0.01099  -0.0903   0.4343   1.0000
   5.750   1.0247   0.02063   0.01143  -0.0897   0.4279   1.0000
   6.000   1.0501   0.02098   0.01175  -0.0894   0.4225   1.0000
   6.250   1.0750   0.02137   0.01214  -0.0890   0.4171   1.0000
   6.500   1.0979   0.02180   0.01265  -0.0883   0.4109   1.0000
   6.750   1.1226   0.02217   0.01302  -0.0878   0.4056   1.0000
   7.000   1.1467   0.02258   0.01344  -0.0873   0.4003   1.0000
   7.250   1.1681   0.02305   0.01403  -0.0864   0.3941   1.0000
   7.500   1.1919   0.02344   0.01442  -0.0858   0.3886   1.0000
   7.750   1.2149   0.02388   0.01490  -0.0852   0.3834   1.0000
   8.000   1.2346   0.02439   0.01554  -0.0840   0.3770   1.0000
   8.250   1.2574   0.02480   0.01597  -0.0833   0.3715   1.0000
   8.500   1.2785   0.02529   0.01652  -0.0823   0.3660   1.0000
   8.750   1.2964   0.02583   0.01721  -0.0809   0.3595   1.0000
   9.000   1.3181   0.02625   0.01764  -0.0800   0.3540   1.0000
   9.250   1.3352   0.02681   0.01832  -0.0785   0.3478   1.0000
   9.500   1.3514   0.02736   0.01898  -0.0769   0.3412   1.0000
   9.750   1.3728   0.02773   0.01933  -0.0759   0.3355   1.0000
  10.000   1.3821   0.02846   0.02028  -0.0734   0.3283   1.0000
  10.250   1.3960   0.02895   0.02082  -0.0714   0.3219   1.0000
  10.500   1.4071   0.02958   0.02154  -0.0691   0.3154   1.0000
  10.750   1.4150   0.03031   0.02241  -0.0664   0.3084   1.0000
  11.000   1.4282   0.03086   0.02296  -0.0645   0.3021   1.0000
  11.250   1.4306   0.03189   0.02419  -0.0615   0.2945   1.0000
  11.500   1.4402   0.03260   0.02492  -0.0594   0.2877   1.0000
  11.750   1.4412   0.03385   0.02635  -0.0568   0.2801   1.0000
  12.000   1.4459   0.03490   0.02746  -0.0546   0.2727   1.0000
  12.250   1.4455   0.03643   0.02915  -0.0523   0.2647   1.0000
  12.500   1.4471   0.03787   0.03065  -0.0504   0.2570   1.0000
  12.750   1.4439   0.03987   0.03279  -0.0486   0.2487   1.0000
  13.000   1.4432   0.04175   0.03471  -0.0471   0.2409   1.0000
  13.250   1.4368   0.04438   0.03750  -0.0459   0.2324   1.0000
  13.500   1.4344   0.04669   0.03982  -0.0449   0.2245   1.0000
  13.750   1.4245   0.05008   0.04339  -0.0444   0.2160   1.0000
  14.000   1.4183   0.05313   0.04647  -0.0440   0.2081   1.0000
  14.250   1.4070   0.05706   0.05053  -0.0441   0.1997   1.0000
  14.500   1.3980   0.06082   0.05437  -0.0443   0.1918   1.0000
  14.750   1.3865   0.06512   0.05875  -0.0449   0.1837   1.0000
  15.000   1.3753   0.06956   0.06326  -0.0456   0.1759   1.0000
  15.250   1.3645   0.07408   0.06782  -0.0466   0.1680   1.0000
  15.500   1.3523   0.07903   0.07287  -0.0479   0.1604   1.0000
  15.750   1.3431   0.08357   0.07739  -0.0490   0.1528   1.0000
  16.000   1.3297   0.08905   0.08299  -0.0508   0.1452   1.0000
  16.250   1.3217   0.09359   0.08749  -0.0522   0.1377   1.0000
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