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EPPLER 554 AIRFOIL (e554-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 554 AIRFOIL (e554-il)
Reynolds number: 500,000
Max Cl/Cd: 103.16 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e554-il-500000.txt
Download as CSV file: xf-e554-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 554 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
  ------ -------- --------- --------- -------- -------- --------
 -17.750  -0.2970   0.16707   0.16480  -0.0248   1.0000   0.0186
 -17.500  -0.6313   0.13346   0.13063  -0.0306   1.0000   0.0094
 -17.250  -0.6791   0.11784   0.11474  -0.0392   1.0000   0.0094
 -17.000  -0.6740   0.11502   0.11193  -0.0403   1.0000   0.0091
 -16.750  -0.7079   0.10371   0.10037  -0.0468   1.0000   0.0092
 -16.500  -0.7200   0.09786   0.09444  -0.0495   1.0000   0.0090
 -16.250  -0.7388   0.09067   0.08709  -0.0534   1.0000   0.0091
 -16.000  -0.7539   0.08449   0.08075  -0.0565   1.0000   0.0090
 -15.750  -0.7688   0.07862   0.07471  -0.0594   1.0000   0.0091
 -15.500  -0.7760   0.07421   0.07018  -0.0613   1.0000   0.0090
 -15.250  -0.7888   0.06907   0.06484  -0.0636   1.0000   0.0091
 -15.000  -0.7942   0.06520   0.06084  -0.0651   1.0000   0.0091
 -14.750  -0.7981   0.06172   0.05725  -0.0661   1.0000   0.0091
 -14.500  -0.8020   0.05830   0.05368  -0.0674   1.0000   0.0092
 -14.000  -0.8053   0.05246   0.04758  -0.0687   1.0000   0.0093
 -13.750  -0.8051   0.04997   0.04500  -0.0681   1.0000   0.0095
 -13.500  -0.8023   0.04786   0.04284  -0.0676   1.0000   0.0096
 -13.250  -0.7984   0.04593   0.04087  -0.0674   1.0000   0.0097
 -13.000  -0.7938   0.04408   0.03897  -0.0671   1.0000   0.0098
 -12.750  -0.7896   0.04225   0.03710  -0.0666   1.0000   0.0099
 -12.500  -0.7851   0.04052   0.03533  -0.0661   1.0000   0.0101
 -12.250  -0.7803   0.03887   0.03363  -0.0655   1.0000   0.0102
 -12.000  -0.7762   0.03724   0.03196  -0.0646   1.0000   0.0104
 -11.750  -0.7723   0.03565   0.03032  -0.0637   1.0000   0.0106
 -11.500  -0.7684   0.03416   0.02879  -0.0626   1.0000   0.0108
 -11.250  -0.7661   0.03267   0.02727  -0.0612   1.0000   0.0109
 -11.000  -0.7648   0.03122   0.02578  -0.0596   1.0000   0.0111
 -10.750  -0.7654   0.02982   0.02434  -0.0577   1.0000   0.0113
 -10.500  -0.7684   0.02850   0.02298  -0.0554   0.9999   0.0115
 -10.250  -0.7381   0.02639   0.02082  -0.0601   0.9947   0.0118
 -10.000  -0.7128   0.02422   0.01863  -0.0643   0.9843   0.0124
  -9.750  -0.6956   0.02248   0.01685  -0.0660   0.9615   0.0129
  -9.500  -0.6609   0.02077   0.01505  -0.0706   0.9452   0.0138
  -9.250  -0.6154   0.01892   0.01313  -0.0775   0.9299   0.0152
  -9.000  -0.5553   0.01747   0.01157  -0.0864   0.9135   0.0177
  -8.750  -0.5033   0.01630   0.01025  -0.0932   0.8821   0.0206
  -8.500  -0.4776   0.01548   0.00925  -0.0943   0.8455   0.0245
  -8.250  -0.4597   0.01480   0.00846  -0.0936   0.8156   0.0300
  -7.250  -0.3799   0.01245   0.00604  -0.0909   0.7365   0.0968
  -7.000  -0.3583   0.01173   0.00545  -0.0906   0.7213   0.1386
  -6.750  -0.3378   0.01068   0.00469  -0.0905   0.7071   0.2156
  -6.500  -0.3162   0.00965   0.00409  -0.0906   0.6938   0.3297
  -6.250  -0.2896   0.00951   0.00399  -0.0906   0.6808   0.3728
  -6.000  -0.2618   0.00953   0.00393  -0.0905   0.6682   0.3947
  -5.750  -0.2338   0.00958   0.00391  -0.0905   0.6570   0.4079
  -5.250  -0.1774   0.00971   0.00383  -0.0905   0.6360   0.4256
  -5.000  -0.1493   0.00979   0.00382  -0.0905   0.6266   0.4338
  -4.750  -0.1208   0.00991   0.00386  -0.0905   0.6171   0.4419
  -4.500  -0.0925   0.00997   0.00380  -0.0905   0.6084   0.4476
  -4.250  -0.0643   0.01006   0.00387  -0.0905   0.5995   0.4542
  -4.000  -0.0357   0.01032   0.00398  -0.0905   0.5916   0.4629
  -3.750  -0.0075   0.01029   0.00397  -0.0905   0.5838   0.4682
  -3.500   0.0207   0.01032   0.00391  -0.0905   0.5769   0.4709
  -3.250   0.0495   0.01031   0.00385  -0.0907   0.5702   0.4739
  -3.000   0.0781   0.01032   0.00378  -0.0908   0.5636   0.4767
  -2.750   0.1067   0.01037   0.00371  -0.0910   0.5576   0.4791
  -2.500   0.1354   0.01029   0.00361  -0.0911   0.5515   0.4818
  -2.250   0.1637   0.01028   0.00355  -0.0912   0.5456   0.4844
  -2.000   0.1921   0.01031   0.00354  -0.0913   0.5404   0.4869
  -1.750   0.2210   0.01030   0.00352  -0.0915   0.5355   0.4895
  -1.500   0.2496   0.01033   0.00349  -0.0917   0.5306   0.4923
  -1.250   0.2782   0.01041   0.00348  -0.0918   0.5259   0.4952
  -1.000   0.3071   0.01046   0.00347  -0.0920   0.5215   0.4976
  -0.750   0.3356   0.01038   0.00343  -0.0922   0.5170   0.5005
  -0.500   0.3641   0.01040   0.00343  -0.0923   0.5128   0.5031
  -0.250   0.3925   0.01048   0.00346  -0.0925   0.5088   0.5058
   0.000   0.4213   0.01054   0.00350  -0.0926   0.5052   0.5088
   0.250   0.4500   0.01057   0.00353  -0.0928   0.5015   0.5120
   0.500   0.4788   0.01063   0.00356  -0.0930   0.4977   0.5148
   0.750   0.5071   0.01063   0.00356  -0.0932   0.4941   0.5178
   1.000   0.5355   0.01075   0.00364  -0.0933   0.4906   0.5207
   1.250   0.5641   0.01078   0.00371  -0.0935   0.4876   0.5238
   1.500   0.5926   0.01082   0.00377  -0.0936   0.4843   0.5270
   1.750   0.6211   0.01088   0.00382  -0.0938   0.4809   0.5303
   2.000   0.6496   0.01096   0.00388  -0.0940   0.4778   0.5335
   2.250   0.6778   0.01105   0.00398  -0.0941   0.4745   0.5372
   2.500   0.7062   0.01114   0.00410  -0.0943   0.4715   0.5407
   2.750   0.7344   0.01119   0.00419  -0.0944   0.4686   0.5444
   3.000   0.7627   0.01126   0.00429  -0.0945   0.4655   0.5481
   3.250   0.7909   0.01133   0.00436  -0.0946   0.4624   0.5516
   3.500   0.8189   0.01141   0.00447  -0.0947   0.4594   0.5555
   3.750   0.8473   0.01161   0.00466  -0.0949   0.4561   0.5596
   4.000   0.8750   0.01166   0.00478  -0.0950   0.4535   0.5642
   4.250   0.9029   0.01174   0.00490  -0.0950   0.4503   0.5686
   4.500   0.9304   0.01178   0.00502  -0.0950   0.4471   0.5732
   4.750   0.9580   0.01187   0.00514  -0.0951   0.4439   0.5779
   5.000   0.9860   0.01207   0.00532  -0.0952   0.4404   0.5830
   5.250   1.0131   0.01215   0.00547  -0.0952   0.4371   0.5880
   5.500   1.0399   0.01218   0.00561  -0.0950   0.4333   0.5934
   5.750   1.0668   0.01226   0.00573  -0.0949   0.4294   0.5996
   6.000   1.0938   0.01238   0.00587  -0.0949   0.4256   0.6059
   6.250   1.1208   0.01254   0.00609  -0.0948   0.4218   0.6123
   6.500   1.1469   0.01259   0.00624  -0.0946   0.4178   0.6195
   6.750   1.1730   0.01265   0.00638  -0.0943   0.4134   0.6265
   7.000   1.1990   0.01276   0.00653  -0.0941   0.4089   0.6345
   7.250   1.2247   0.01290   0.00674  -0.0938   0.4043   0.6430
   7.500   1.2500   0.01295   0.00691  -0.0934   0.3993   0.6526
   7.750   1.2750   0.01303   0.00707  -0.0930   0.3942   0.6625
   8.000   1.2997   0.01320   0.00728  -0.0926   0.3889   0.6737
   8.250   1.3242   0.01324   0.00747  -0.0921   0.3827   0.6853
   8.500   1.3476   0.01337   0.00766  -0.0914   0.3763   0.6981
   8.750   1.3713   0.01348   0.00789  -0.0908   0.3695   0.7129
   9.000   1.3938   0.01360   0.00811  -0.0899   0.3615   0.7299
   9.250   1.4160   0.01375   0.00837  -0.0890   0.3533   0.7491
   9.500   1.4358   0.01394   0.00864  -0.0878   0.3435   0.7716
   9.750   1.4556   0.01411   0.00894  -0.0864   0.3320   0.7987
  10.000   1.4712   0.01433   0.00928  -0.0844   0.3188   0.8362
  10.250   1.4765   0.01440   0.00954  -0.0801   0.3059   1.0000
  10.500   1.4888   0.01492   0.01000  -0.0777   0.2896   1.0000
  10.750   1.4983   0.01556   0.01058  -0.0750   0.2720   1.0000
  11.000   1.5047   0.01637   0.01130  -0.0720   0.2536   1.0000
  11.250   1.5075   0.01734   0.01220  -0.0687   0.2354   1.0000
  11.500   1.5095   0.01842   0.01322  -0.0655   0.2170   1.0000
  11.750   1.5093   0.01969   0.01443  -0.0623   0.2005   1.0000
  12.000   1.5077   0.02115   0.01584  -0.0593   0.1859   1.0000
  12.250   1.5046   0.02286   0.01752  -0.0566   0.1723   1.0000
  12.500   1.5004   0.02484   0.01947  -0.0543   0.1601   1.0000
  12.750   1.4965   0.02700   0.02163  -0.0524   0.1490   1.0000
  13.000   1.4930   0.02933   0.02397  -0.0510   0.1383   1.0000
  13.250   1.4879   0.03196   0.02661  -0.0497   0.1291   1.0000
  13.500   1.4799   0.03501   0.02966  -0.0487   0.1203   1.0000
  13.750   1.4748   0.03795   0.03262  -0.0480   0.1116   1.0000
  14.000   1.4680   0.04115   0.03584  -0.0475   0.1044   1.0000
  14.250   1.4598   0.04462   0.03933  -0.0472   0.0975   1.0000
  14.500   1.4542   0.04793   0.04268  -0.0471   0.0912   1.0000
  14.750   1.4451   0.05173   0.04649  -0.0471   0.0851   1.0000
  15.000   1.4406   0.05516   0.04997  -0.0473   0.0794   1.0000
  15.250   1.4316   0.05921   0.05403  -0.0477   0.0739   1.0000
  15.500   1.4282   0.06270   0.05757  -0.0482   0.0690   1.0000
  15.750   1.4202   0.06687   0.06176  -0.0489   0.0642   1.0000
  16.000   1.4169   0.07053   0.06548  -0.0496   0.0595   1.0000
  16.250   1.4101   0.07473   0.06970  -0.0505   0.0552   1.0000
  16.500   1.4070   0.07853   0.07354  -0.0514   0.0511   1.0000
  16.750   1.4009   0.08282   0.07786  -0.0526   0.0476   1.0000
  17.000   1.3981   0.08672   0.08181  -0.0537   0.0441   1.0000
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