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EPPLER E852 AIRFOIL (e852-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER E852 AIRFOIL (e852-il)
Reynolds number: 100,000
Max Cl/Cd: 57.3 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e852-il-100000-n5.txt
Download as CSV file: xf-e852-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER E852 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4281   0.09239   0.08755  -0.0453   1.0000   0.0176
  -9.000  -0.4329   0.08846   0.08370  -0.0462   1.0000   0.0174
  -8.750  -0.4390   0.08460   0.07992  -0.0469   1.0000   0.0172
  -8.500  -0.4478   0.08061   0.07602  -0.0476   1.0000   0.0170
  -8.250  -0.4598   0.07660   0.07211  -0.0482   1.0000   0.0168
  -8.000  -0.4763   0.07283   0.06845  -0.0484   1.0000   0.0166
  -7.750  -0.4980   0.06959   0.06529  -0.0481   1.0000   0.0165
  -7.500  -0.5161   0.06611   0.06183  -0.0485   1.0000   0.0164
  -7.250  -0.5130   0.05989   0.05542  -0.0547   0.9947   0.0161
  -7.000  -0.4991   0.05330   0.04849  -0.0614   0.9868   0.0158
  -6.750  -0.4798   0.04728   0.04203  -0.0667   0.9806   0.0155
  -6.500  -0.4605   0.04221   0.03646  -0.0697   0.9734   0.0154
  -6.250  -0.4337   0.03743   0.03107  -0.0728   0.9690   0.0153
  -6.000  -0.4109   0.03375   0.02672  -0.0738   0.9626   0.0153
  -5.750  -0.3815   0.03038   0.02276  -0.0752   0.9586   0.0155
  -5.500  -0.3505   0.02759   0.01947  -0.0764   0.9554   0.0160
  -5.250  -0.3245   0.02548   0.01701  -0.0762   0.9500   0.0169
  -5.000  -0.2939   0.02386   0.01510  -0.0770   0.9464   0.0200
  -4.750  -0.2623   0.02228   0.01345  -0.0784   0.9437   0.0250
  -4.500  -0.2369   0.02097   0.01193  -0.0780   0.9382   0.0301
  -4.250  -0.2069   0.01977   0.01071  -0.0791   0.9342   0.0456
  -4.000  -0.1736   0.01859   0.00956  -0.0807   0.9314   0.0803
  -3.750  -0.1457   0.01731   0.00868  -0.0818   0.9269   0.1678
  -3.500  -0.1195   0.01601   0.00839  -0.0827   0.9226   0.4182
  -3.250  -0.0877   0.01592   0.00835  -0.0834   0.9192   0.5058
  -3.000  -0.0557   0.01592   0.00825  -0.0842   0.9161   0.5501
  -2.750  -0.0314   0.01598   0.00825  -0.0834   0.9103   0.5816
  -2.500  -0.0010   0.01600   0.00823  -0.0837   0.9068   0.6147
  -2.250   0.0324   0.01596   0.00810  -0.0846   0.9044   0.6373
  -2.000   0.0568   0.01598   0.00798  -0.0841   0.8985   0.6505
  -1.750   0.0877   0.01593   0.00783  -0.0848   0.8947   0.6625
  -1.500   0.1216   0.01586   0.00767  -0.0861   0.8921   0.6743
  -1.250   0.1496   0.01586   0.00760  -0.0863   0.8876   0.6860
  -1.000   0.1767   0.01587   0.00758  -0.0863   0.8828   0.6971
  -0.750   0.2086   0.01582   0.00747  -0.0872   0.8796   0.7089
  -0.500   0.2425   0.01575   0.00738  -0.0884   0.8773   0.7215
  -0.250   0.2634   0.01588   0.00752  -0.0873   0.8705   0.7342
   0.000   0.2941   0.01586   0.00752  -0.0879   0.8670   0.7483
   0.250   0.3271   0.01580   0.00750  -0.0890   0.8645   0.7634
   0.500   0.3480   0.01594   0.00769  -0.0878   0.8579   0.7801
   0.750   0.3767   0.01592   0.00774  -0.0879   0.8540   0.7979
   1.000   0.4083   0.01584   0.00774  -0.0885   0.8512   0.8190
   1.250   0.4268   0.01596   0.00798  -0.0868   0.8441   0.8446
   1.500   0.4557   0.01588   0.00806  -0.0868   0.8401   0.8770
   1.750   0.4937   0.01573   0.00803  -0.0886   0.8374   0.9231
   2.000   0.5232   0.01589   0.00827  -0.0895   0.8298   1.0000
   2.250   0.5582   0.01591   0.00833  -0.0911   0.8257   1.0000
   2.500   0.5840   0.01612   0.00864  -0.0910   0.8185   1.0000
   2.750   0.6176   0.01611   0.00872  -0.0921   0.8129   1.0000
   3.000   0.6442   0.01624   0.00893  -0.0919   0.8044   1.0000
   3.250   0.6816   0.01604   0.00885  -0.0934   0.7977   1.0000
   3.500   0.7091   0.01599   0.00892  -0.0930   0.7857   1.0000
   3.750   0.7408   0.01569   0.00873  -0.0929   0.7704   1.0000
   4.000   0.7657   0.01545   0.00868  -0.0915   0.7482   1.0000
   4.250   0.7913   0.01521   0.00855  -0.0902   0.7229   1.0000
   4.500   0.8157   0.01508   0.00852  -0.0888   0.6939   1.0000
   4.750   0.8371   0.01501   0.00854  -0.0869   0.6532   1.0000
   5.000   0.8589   0.01499   0.00834  -0.0847   0.5655   1.0000
   5.250   0.8683   0.01609   0.00842  -0.0806   0.3942   1.0000
   5.500   0.8711   0.01783   0.00931  -0.0766   0.2510   1.0000
   5.750   0.8793   0.01948   0.01030  -0.0738   0.1459   1.0000
   6.000   0.8929   0.02081   0.01134  -0.0717   0.0954   1.0000
   6.250   0.9068   0.02216   0.01261  -0.0696   0.0622   1.0000
   6.500   0.9200   0.02363   0.01399  -0.0673   0.0417   1.0000
   6.750   0.9327   0.02524   0.01561  -0.0649   0.0282   1.0000
   7.000   0.9479   0.02661   0.01704  -0.0631   0.0192   1.0000
   7.250   0.9622   0.02855   0.01916  -0.0608   0.0164   1.0000
   7.500   0.9824   0.03064   0.02144  -0.0595   0.0145   1.0000
   7.750   1.0032   0.03243   0.02341  -0.0585   0.0122   1.0000
   8.000   1.0200   0.03475   0.02587  -0.0575   0.0099   1.0000
   8.250   1.0411   0.03733   0.02878  -0.0565   0.0089   1.0000
   8.500   1.0597   0.04008   0.03194  -0.0552   0.0083   1.0000
   8.750   1.0733   0.04335   0.03564  -0.0533   0.0081   1.0000
   9.000   1.0808   0.04679   0.03953  -0.0508   0.0079   1.0000
   9.250   1.0820   0.05026   0.04342  -0.0477   0.0079   1.0000
   9.500   1.0775   0.05358   0.04711  -0.0442   0.0078   1.0000
   9.750   1.0687   0.05701   0.05088  -0.0407   0.0078   1.0000
  10.000   1.0570   0.06053   0.05469  -0.0376   0.0079   1.0000
  10.250   1.0427   0.06428   0.05872  -0.0351   0.0079   1.0000
  10.500   1.0267   0.06831   0.06300  -0.0334   0.0079   1.0000
  10.750   1.0096   0.07271   0.06763  -0.0327   0.0080   1.0000
  11.000   0.9905   0.07777   0.07289  -0.0330   0.0080   1.0000
  11.250   0.9713   0.08336   0.07867  -0.0346   0.0081   1.0000
  11.500   0.9518   0.08977   0.08523  -0.0375   0.0081   1.0000
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