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EPPLER 556 AIRFOIL (e556-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 556 AIRFOIL (e556-il)
Reynolds number: 50,000
Max Cl/Cd: 25.5 at α=11.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e556-il-50000.txt
Download as CSV file: xf-e556-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 556 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4240   0.11459   0.10752  -0.0482   1.0000   0.1401
 -11.000  -0.4207   0.10992   0.10287  -0.0485   1.0000   0.1374
 -10.750  -0.5266   0.08844   0.08164  -0.0646   1.0000   0.1104
 -10.500  -0.5325   0.08359   0.07684  -0.0649   1.0000   0.1093
 -10.250  -0.5524   0.07834   0.07164  -0.0659   1.0000   0.1080
 -10.000  -0.5807   0.07352   0.06687  -0.0665   1.0000   0.1062
  -9.750  -0.6163   0.06967   0.06306  -0.0658   1.0000   0.1042
  -9.500  -0.7052   0.06535   0.05826  -0.0655   1.0000   0.0964
  -9.250  -0.7163   0.06190   0.05458  -0.0642   1.0000   0.0963
  -9.000  -0.7207   0.05806   0.05064  -0.0629   1.0000   0.0972
  -8.750  -0.7171   0.05482   0.04731  -0.0616   1.0000   0.0987
  -8.500  -0.7132   0.05181   0.04414  -0.0602   1.0000   0.1006
  -8.250  -0.7081   0.04875   0.04081  -0.0591   1.0000   0.1019
  -8.000  -0.6997   0.04597   0.03774  -0.0581   1.0000   0.1051
  -7.750  -0.6898   0.04329   0.03448  -0.0575   1.0000   0.1099
  -7.500  -0.6743   0.04089   0.03221  -0.0559   1.0000   0.1163
  -7.250  -0.6584   0.03874   0.02972  -0.0548   1.0000   0.1253
  -7.000  -0.6424   0.03693   0.02802  -0.0530   1.0000   0.1375
  -6.750  -0.6268   0.03518   0.02630  -0.0512   1.0000   0.1535
  -6.500  -0.6133   0.03346   0.02494  -0.0489   1.0000   0.1748
  -6.250  -0.5991   0.03131   0.02319  -0.0479   1.0000   0.2111
  -6.000  -0.5852   0.02973   0.02317  -0.0466   1.0000   0.3132
  -5.750  -0.5790   0.03515   0.02905  -0.0366   1.0000   0.4161
  -5.500  -0.5718   0.03918   0.03299  -0.0284   1.0000   0.4583
  -5.250  -0.5673   0.04309   0.03690  -0.0183   1.0000   0.4795
  -5.000  -0.5597   0.04524   0.03893  -0.0119   1.0000   0.5072
  -4.750  -0.5537   0.04761   0.04124  -0.0036   1.0000   0.5271
  -4.500  -0.5464   0.04876   0.04228   0.0021   1.0000   0.5509
  -4.250  -0.5396   0.04940   0.04281   0.0072   1.0000   0.5732
  -4.000  -0.5326   0.05008   0.04339   0.0130   1.0000   0.5933
  -3.750  -0.5255   0.05005   0.04326   0.0168   1.0000   0.6142
  -3.500  -0.5178   0.04942   0.04248   0.0184   1.0000   0.6349
  -3.250  -0.5105   0.04913   0.04209   0.0220   1.0000   0.6517
  -3.000  -0.5017   0.04854   0.04139   0.0241   1.0000   0.6673
  -2.750  -0.4926   0.04799   0.04074   0.0266   1.0000   0.6803
  -2.500  -0.4825   0.04729   0.03991   0.0283   1.0000   0.6911
  -2.250  -0.4687   0.04632   0.03880   0.0275   1.0000   0.7009
  -2.000  -0.4519   0.04570   0.03806   0.0273   0.9988   0.7093
  -1.750  -0.4062   0.04572   0.03783   0.0212   0.9864   0.7182
  -1.500  -0.3644   0.04565   0.03754   0.0159   0.9746   0.7257
  -1.250  -0.3237   0.04541   0.03709   0.0103   0.9629   0.7320
  -1.000  -0.2915   0.04520   0.03674   0.0074   0.9517   0.7374
  -0.750  -0.2544   0.04503   0.03641   0.0027   0.9401   0.7429
  -0.500  -0.2172   0.04497   0.03620  -0.0017   0.9291   0.7480
  -0.250  -0.1784   0.04508   0.03618  -0.0056   0.9180   0.7529
   0.000  -0.1466   0.04502   0.03601  -0.0089   0.9066   0.7580
   0.250  -0.1132   0.04507   0.03596  -0.0125   0.8952   0.7631
   0.500  -0.0801   0.04524   0.03605  -0.0151   0.8845   0.7679
   0.750  -0.0409   0.04550   0.03622  -0.0192   0.8735   0.7738
   1.000  -0.0139   0.04568   0.03635  -0.0216   0.8620   0.7789
   1.250   0.0145   0.04596   0.03658  -0.0233   0.8514   0.7842
   1.500   0.0602   0.04640   0.03694  -0.0280   0.8406   0.7907
   1.750   0.0779   0.04671   0.03725  -0.0286   0.8294   0.7962
   2.000   0.1047   0.04716   0.03768  -0.0301   0.8185   0.8025
   2.250   0.1476   0.04769   0.03817  -0.0343   0.8080   0.8097
   2.500   0.1653   0.04818   0.03868  -0.0344   0.7970   0.8160
   2.750   0.1925   0.04888   0.03937  -0.0365   0.7859   0.8235
   3.000   0.2275   0.04934   0.03985  -0.0384   0.7762   0.8318
   3.250   0.2499   0.05012   0.04066  -0.0399   0.7647   0.8398
   3.500   0.2666   0.05087   0.04145  -0.0398   0.7543   0.8479
   3.750   0.3025   0.05144   0.04205  -0.0420   0.7441   0.8584
   4.000   0.3206   0.05228   0.04294  -0.0424   0.7329   0.8689
   4.250   0.3353   0.05323   0.04397  -0.0423   0.7223   0.8797
   4.500   0.3674   0.05377   0.04458  -0.0437   0.7120   0.8938
   4.750   0.3830   0.05473   0.04563  -0.0438   0.7012   0.9090
   5.000   0.3988   0.05583   0.04685  -0.0442   0.6900   0.9282
   5.500   0.4830   0.05763   0.04888  -0.0522   0.6654   1.0000
   5.750   0.5119   0.05938   0.05070  -0.0559   0.6525   1.0000
   6.000   0.5381   0.06132   0.05268  -0.0592   0.6390   1.0000
   6.250   0.5678   0.06321   0.05463  -0.0627   0.6256   1.0000
   6.500   0.6015   0.06490   0.05638  -0.0661   0.6118   1.0000
   6.750   0.6365   0.06646   0.05800  -0.0693   0.5981   1.0000
   7.000   0.6734   0.06776   0.05935  -0.0720   0.5841   1.0000
   7.250   0.7162   0.06848   0.06015  -0.0744   0.5704   1.0000
   7.500   0.7440   0.06989   0.06162  -0.0757   0.5563   1.0000
   7.750   0.7570   0.07216   0.06393  -0.0762   0.5416   1.0000
   8.000   0.7679   0.07462   0.06645  -0.0765   0.5272   1.0000
   8.250   0.7821   0.07678   0.06867  -0.0767   0.5125   1.0000
   8.500   0.7959   0.07897   0.07092  -0.0768   0.4979   1.0000
   8.750   0.8101   0.08110   0.07313  -0.0768   0.4833   1.0000
   9.000   0.8245   0.08321   0.07530  -0.0766   0.4687   1.0000
   9.250   0.8390   0.08530   0.07750  -0.0764   0.4542   1.0000
   9.500   0.8546   0.08718   0.07947  -0.0761   0.4394   1.0000
   9.750   0.8704   0.08909   0.08147  -0.0757   0.4250   1.0000
  10.000   0.8877   0.09070   0.08318  -0.0751   0.4103   1.0000
  10.250   0.9081   0.09192   0.08454  -0.0744   0.3960   1.0000
  10.500   0.9279   0.09298   0.08572  -0.0734   0.3812   1.0000
  10.750   0.9561   0.09280   0.08569  -0.0719   0.3667   1.0000
  11.000   1.1530   0.06679   0.06027  -0.0613   0.3415   1.0000
  11.250   0.9027   0.10827   0.10114  -0.0760   0.3440   1.0000
  11.500   1.3519   0.05301   0.04619  -0.0614   0.2701   1.0000
  11.750   1.1137   0.08089   0.07451  -0.0599   0.3037   1.0000
  12.000   0.9516   0.11350   0.10673  -0.0740   0.3050   1.0000
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