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E10(08%) (e228-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: E10(08%) (e228-il)
Reynolds number: 200,000
Max Cl/Cd: 48.2 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e228-il-200000-n5.txt
Download as CSV file: xf-e228-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E10(08%)                                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.7837   0.08871   0.08529   0.0008   1.0000   0.0107
 -12.000  -0.8212   0.07459   0.07104  -0.0092   1.0000   0.0100
 -11.750  -0.8501   0.06441   0.06065  -0.0173   1.0000   0.0097
 -11.500  -0.8732   0.05725   0.05328  -0.0225   1.0000   0.0096
 -11.250  -0.8928   0.05198   0.04779  -0.0251   1.0000   0.0095
 -11.000  -0.9083   0.04812   0.04370  -0.0254   1.0000   0.0096
 -10.750  -0.9235   0.04466   0.03999  -0.0240   1.0000   0.0096
 -10.500  -0.9332   0.04194   0.03702  -0.0215   1.0000   0.0098
 -10.250  -0.9348   0.03959   0.03441  -0.0193   1.0000   0.0102
 -10.000  -0.9325   0.03701   0.03151  -0.0174   1.0000   0.0107
  -9.750  -0.9242   0.03500   0.02917  -0.0157   1.0000   0.0115
  -9.500  -0.9129   0.03309   0.02691  -0.0141   1.0000   0.0121
  -9.250  -0.9019   0.03059   0.02408  -0.0125   1.0000   0.0125
  -9.000  -0.8892   0.02821   0.02147  -0.0111   1.0000   0.0132
  -8.750  -0.8725   0.02664   0.01977  -0.0099   1.0000   0.0138
  -8.500  -0.8543   0.02526   0.01825  -0.0089   1.0000   0.0147
  -8.250  -0.8352   0.02395   0.01678  -0.0078   1.0000   0.0156
  -8.000  -0.8146   0.02295   0.01561  -0.0069   1.0000   0.0171
  -7.750  -0.7939   0.02192   0.01443  -0.0059   1.0000   0.0185
  -7.500  -0.7764   0.02044   0.01288  -0.0046   1.0000   0.0200
  -7.250  -0.7561   0.01947   0.01180  -0.0035   1.0000   0.0213
  -7.000  -0.7347   0.01870   0.01095  -0.0026   1.0000   0.0233
  -6.750  -0.7129   0.01801   0.01015  -0.0017   1.0000   0.0255
  -6.500  -0.6926   0.01713   0.00917  -0.0005   1.0000   0.0272
  -6.250  -0.6722   0.01633   0.00831   0.0007   1.0000   0.0300
  -6.000  -0.6507   0.01572   0.00764   0.0018   1.0000   0.0335
  -5.750  -0.6300   0.01511   0.00699   0.0030   1.0000   0.0399
  -5.500  -0.6106   0.01446   0.00640   0.0044   1.0000   0.0554
  -5.250  -0.5923   0.01385   0.00591   0.0059   1.0000   0.0808
  -5.000  -0.5740   0.01336   0.00552   0.0075   1.0000   0.1068
  -4.750  -0.5427   0.01287   0.00513   0.0063   0.9929   0.1400
  -4.500  -0.5089   0.01232   0.00477   0.0046   0.9847   0.1843
  -4.250  -0.4769   0.01174   0.00448   0.0032   0.9755   0.2469
  -4.000  -0.4439   0.01130   0.00419   0.0018   0.9668   0.2979
  -3.750  -0.4117   0.01094   0.00396   0.0007   0.9572   0.3414
  -3.500  -0.3813   0.01062   0.00377   0.0001   0.9464   0.3838
  -3.250  -0.3520   0.01033   0.00359  -0.0003   0.9354   0.4246
  -3.000  -0.3239   0.01008   0.00342  -0.0003   0.9238   0.4633
  -2.750  -0.2972   0.00986   0.00329   0.0001   0.9118   0.5008
  -2.500  -0.2716   0.00965   0.00317   0.0008   0.8994   0.5373
  -2.250  -0.2468   0.00946   0.00307   0.0017   0.8865   0.5733
  -2.000  -0.2225   0.00928   0.00297   0.0027   0.8732   0.6088
  -1.750  -0.1981   0.00913   0.00289   0.0038   0.8598   0.6443
  -1.500  -0.1736   0.00898   0.00283   0.0049   0.8461   0.6789
  -1.250  -0.1488   0.00886   0.00278   0.0059   0.8323   0.7128
  -1.000  -0.1236   0.00876   0.00274   0.0069   0.8182   0.7454
  -0.750  -0.0978   0.00869   0.00271   0.0077   0.8038   0.7761
  -0.500  -0.0711   0.00864   0.00270   0.0084   0.7892   0.8050
  -0.250  -0.0432   0.00863   0.00269   0.0089   0.7740   0.8317
   0.000  -0.0140   0.00865   0.00270   0.0091   0.7583   0.8563
   0.250   0.0179   0.00869   0.00272   0.0086   0.7413   0.8771
   0.500   0.0505   0.00875   0.00275   0.0080   0.7235   0.8959
   0.750   0.0839   0.00883   0.00278   0.0072   0.7050   0.9120
   1.000   0.1184   0.00893   0.00281   0.0060   0.6854   0.9256
   1.250   0.1537   0.00904   0.00286   0.0047   0.6643   0.9370
   1.500   0.1884   0.00915   0.00291   0.0035   0.6425   0.9474
   1.750   0.2220   0.00928   0.00296   0.0024   0.6194   0.9574
   2.000   0.2570   0.00942   0.00303   0.0010   0.5948   0.9660
   2.250   0.2925   0.00955   0.00309  -0.0006   0.5686   0.9736
   2.500   0.3264   0.00971   0.00317  -0.0018   0.5413   0.9819
   2.750   0.3637   0.00986   0.00322  -0.0039   0.5107   0.9878
   3.000   0.3993   0.01004   0.00332  -0.0057   0.4788   0.9942
   3.250   0.4361   0.01022   0.00341  -0.0078   0.4446   0.9996
   3.500   0.4597   0.01042   0.00352  -0.0071   0.4144   1.0000
   3.750   0.4822   0.01066   0.00366  -0.0062   0.3837   1.0000
   4.000   0.5047   0.01092   0.00386  -0.0054   0.3527   1.0000
   4.250   0.5271   0.01122   0.00406  -0.0045   0.3217   1.0000
   4.500   0.5495   0.01154   0.00429  -0.0036   0.2889   1.0000
   4.750   0.5716   0.01192   0.00456  -0.0028   0.2556   1.0000
   5.000   0.5936   0.01233   0.00486  -0.0019   0.2229   1.0000
   5.250   0.6155   0.01277   0.00519  -0.0010   0.1904   1.0000
   5.500   0.6371   0.01325   0.00561  -0.0001   0.1605   1.0000
   5.750   0.6586   0.01376   0.00602   0.0009   0.1333   1.0000
   6.000   0.6800   0.01428   0.00648   0.0018   0.1107   1.0000
   6.250   0.7011   0.01485   0.00698   0.0028   0.0906   1.0000
   6.500   0.7222   0.01542   0.00753   0.0038   0.0755   1.0000
   6.750   0.7430   0.01602   0.00812   0.0049   0.0614   1.0000
   7.000   0.7635   0.01666   0.00876   0.0059   0.0481   1.0000
   7.250   0.7836   0.01731   0.00939   0.0070   0.0367   1.0000
   7.500   0.8028   0.01810   0.01015   0.0082   0.0287   1.0000
   7.750   0.8226   0.01881   0.01098   0.0094   0.0235   1.0000
   8.000   0.8397   0.01986   0.01208   0.0110   0.0193   1.0000
   8.250   0.8579   0.02073   0.01307   0.0123   0.0164   1.0000
   8.500   0.8737   0.02186   0.01424   0.0138   0.0142   1.0000
   8.750   0.8913   0.02276   0.01532   0.0152   0.0127   1.0000
   9.000   0.9068   0.02390   0.01660   0.0167   0.0117   1.0000
   9.250   0.9215   0.02508   0.01791   0.0183   0.0110   1.0000
   9.500   0.9351   0.02633   0.01928   0.0199   0.0104   1.0000
   9.750   0.9468   0.02775   0.02082   0.0216   0.0100   1.0000
  10.000   0.9556   0.02944   0.02265   0.0236   0.0096   1.0000
  10.250   0.9612   0.03153   0.02491   0.0257   0.0093   1.0000
  10.500   0.9679   0.03329   0.02687   0.0277   0.0092   1.0000
  10.750   0.9695   0.03520   0.02900   0.0303   0.0090   1.0000
  11.000   0.9689   0.03726   0.03127   0.0325   0.0089   1.0000
  11.250   0.9651   0.03976   0.03400   0.0343   0.0088   1.0000
  11.500   0.9602   0.04246   0.03693   0.0354   0.0087   1.0000
  11.750   0.9528   0.04563   0.04033   0.0357   0.0086   1.0000
  12.000   0.9442   0.04920   0.04410   0.0352   0.0086   1.0000
  12.250   0.9323   0.05354   0.04868   0.0336   0.0083   1.0000
  12.500   0.9198   0.05841   0.05376   0.0312   0.0084   1.0000
  12.750   0.9054   0.06410   0.05965   0.0278   0.0084   1.0000
  13.000   0.8870   0.07112   0.06686   0.0231   0.0084   1.0000
  13.250   0.8692   0.07866   0.07457   0.0180   0.0083   1.0000
  13.500   0.8480   0.08723   0.08325   0.0126   0.0088   1.0000
  13.750   0.8215   0.09800   0.09416   0.0058   0.0088   1.0000
  14.000   0.7981   0.10841   0.10465  -0.0001   0.0091   1.0000
  14.250   0.7696   0.12096   0.11726  -0.0067   0.0093   1.0000
  14.500   0.7413   0.13443   0.13076  -0.0130   0.0095   1.0000
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