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S4062-095-87 (s4062-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S4062-095-87 (s4062-il)
Reynolds number: 500,000
Max Cl/Cd: 114.52 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4062-il-500000-n5.txt
Download as CSV file: xf-s4062-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4062-095-87                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2782   0.08257   0.08007  -0.0614   0.9085   0.0065
  -9.000  -0.2801   0.07815   0.07562  -0.0632   0.8982   0.0066
  -8.750  -0.2825   0.07408   0.07153  -0.0649   0.8882   0.0065
  -8.500  -0.2867   0.06992   0.06738  -0.0668   0.8785   0.0064
  -8.250  -0.3027   0.06405   0.06150  -0.0691   0.8678   0.0066
  -8.000  -0.3170   0.05750   0.05494  -0.0744   0.8577   0.0066
  -7.750  -0.3658   0.02850   0.02498  -0.0971   0.8440   0.0062
  -7.500  -0.3503   0.02419   0.02008  -0.0985   0.8388   0.0063
  -7.250  -0.3287   0.02192   0.01741  -0.0990   0.8339   0.0065
  -7.000  -0.3055   0.02017   0.01528  -0.0992   0.8297   0.0067
  -6.750  -0.2817   0.01839   0.01316  -0.0993   0.8255   0.0067
  -6.500  -0.2575   0.01659   0.01104  -0.0993   0.8209   0.0068
  -6.250  -0.2323   0.01529   0.00950  -0.0993   0.8167   0.0070
  -6.000  -0.2063   0.01436   0.00840  -0.0992   0.8131   0.0073
  -5.750  -0.1794   0.01360   0.00753  -0.0993   0.8087   0.0075
  -5.500  -0.1524   0.01297   0.00677  -0.0993   0.8044   0.0078
  -5.250  -0.1253   0.01240   0.00609  -0.0992   0.8006   0.0082
  -5.000  -0.0979   0.01189   0.00547  -0.0992   0.7967   0.0087
  -4.750  -0.0702   0.01144   0.00493  -0.0993   0.7923   0.0091
  -4.500  -0.0424   0.01105   0.00444  -0.0993   0.7882   0.0096
  -4.250  -0.0148   0.01062   0.00392  -0.0993   0.7845   0.0106
  -4.000   0.0132   0.01033   0.00359  -0.0993   0.7803   0.0121
  -3.750   0.0413   0.01004   0.00324  -0.0994   0.7759   0.0136
  -3.500   0.0693   0.00974   0.00289  -0.0994   0.7720   0.0173
  -3.250   0.0973   0.00945   0.00262  -0.0994   0.7682   0.0280
  -3.000   0.1254   0.00920   0.00242  -0.0995   0.7637   0.0450
  -2.750   0.1535   0.00899   0.00225  -0.0996   0.7595   0.0644
  -2.500   0.1815   0.00880   0.00211  -0.0997   0.7556   0.0882
  -2.250   0.2097   0.00860   0.00200  -0.0998   0.7513   0.1164
  -2.000   0.2378   0.00844   0.00191  -0.0999   0.7468   0.1433
  -1.750   0.2660   0.00831   0.00181  -0.1000   0.7427   0.1679
  -1.500   0.2941   0.00818   0.00173  -0.1001   0.7386   0.1964
  -1.250   0.3224   0.00804   0.00168  -0.1002   0.7339   0.2299
  -1.000   0.3505   0.00792   0.00163  -0.1003   0.7293   0.2651
  -0.750   0.3785   0.00780   0.00159  -0.1004   0.7251   0.3074
  -0.500   0.4066   0.00766   0.00158  -0.1005   0.7199   0.3556
  -0.250   0.4344   0.00750   0.00157  -0.1006   0.7146   0.4152
   0.000   0.4621   0.00735   0.00157  -0.1006   0.7091   0.4801
   0.250   0.4895   0.00717   0.00158  -0.1005   0.7013   0.5541
   0.500   0.5162   0.00697   0.00161  -0.1003   0.6929   0.6398
   0.750   0.5416   0.00674   0.00164  -0.0997   0.6835   0.7405
   1.000   0.5635   0.00646   0.00169  -0.0981   0.6744   0.8613
   1.250   0.5995   0.00632   0.00164  -0.0996   0.6654   1.0000
   1.500   0.6272   0.00640   0.00167  -0.0996   0.6564   1.0000
   1.750   0.6549   0.00648   0.00170  -0.0995   0.6474   1.0000
   2.000   0.6824   0.00657   0.00174  -0.0994   0.6376   1.0000
   2.250   0.7098   0.00667   0.00179  -0.0993   0.6266   1.0000
   2.500   0.7372   0.00677   0.00186  -0.0993   0.6152   1.0000
   2.750   0.7644   0.00689   0.00193  -0.0991   0.6026   1.0000
   3.000   0.7913   0.00702   0.00202  -0.0990   0.5880   1.0000
   3.250   0.8179   0.00718   0.00212  -0.0988   0.5711   1.0000
   3.500   0.8440   0.00737   0.00223  -0.0985   0.5510   1.0000
   3.750   0.8695   0.00762   0.00237  -0.0981   0.5247   1.0000
   4.000   0.8943   0.00792   0.00256  -0.0976   0.4943   1.0000
   4.250   0.9181   0.00830   0.00278  -0.0970   0.4569   1.0000
   4.500   0.9410   0.00876   0.00305  -0.0963   0.4162   1.0000
   5.000   0.9863   0.00973   0.00369  -0.0949   0.3426   1.0000
   5.250   1.0090   0.01020   0.00402  -0.0942   0.3109   1.0000
   5.500   1.0313   0.01069   0.00436  -0.0934   0.2799   1.0000
   6.000   1.0751   0.01169   0.00510  -0.0918   0.2226   1.0000
   6.250   1.0979   0.01210   0.00545  -0.0912   0.2053   1.0000
   6.500   1.1200   0.01254   0.00581  -0.0904   0.1855   1.0000
   6.750   1.1408   0.01307   0.00624  -0.0895   0.1630   1.0000
   7.000   1.1617   0.01357   0.00666  -0.0885   0.1426   1.0000
   7.250   1.1820   0.01409   0.00710  -0.0875   0.1241   1.0000
   7.500   1.2014   0.01466   0.00758  -0.0863   0.1056   1.0000
   7.750   1.2202   0.01524   0.00808  -0.0851   0.0886   1.0000
   8.000   1.2379   0.01587   0.00864  -0.0837   0.0727   1.0000
   8.250   1.2559   0.01644   0.00917  -0.0824   0.0617   1.0000
   8.500   1.2724   0.01700   0.00972  -0.0807   0.0527   1.0000
   8.750   1.2874   0.01759   0.01030  -0.0789   0.0451   1.0000
   9.000   1.3016   0.01825   0.01094  -0.0769   0.0379   1.0000
   9.250   1.3152   0.01896   0.01164  -0.0750   0.0309   1.0000
   9.500   1.3287   0.01971   0.01240  -0.0731   0.0242   1.0000
   9.750   1.3417   0.02051   0.01320  -0.0713   0.0191   1.0000
  10.000   1.3544   0.02136   0.01407  -0.0695   0.0159   1.0000
  10.250   1.3671   0.02223   0.01497  -0.0678   0.0142   1.0000
  10.500   1.3792   0.02318   0.01597  -0.0660   0.0129   1.0000
  10.750   1.3920   0.02409   0.01697  -0.0645   0.0122   1.0000
  11.000   1.4042   0.02506   0.01803  -0.0629   0.0116   1.0000
  11.250   1.4156   0.02612   0.01917  -0.0613   0.0111   1.0000
  11.500   1.4257   0.02731   0.02043  -0.0598   0.0105   1.0000
  11.750   1.4345   0.02863   0.02183  -0.0582   0.0099   1.0000
  12.000   1.4406   0.03021   0.02351  -0.0564   0.0095   1.0000
  12.250   1.4490   0.03163   0.02503  -0.0550   0.0092   1.0000
  12.500   1.4568   0.03313   0.02663  -0.0536   0.0091   1.0000
  12.750   1.4638   0.03473   0.02836  -0.0523   0.0088   1.0000
  13.000   1.4698   0.03648   0.03022  -0.0511   0.0086   1.0000
  13.250   1.4751   0.03834   0.03218  -0.0499   0.0083   1.0000
  13.500   1.4792   0.04036   0.03431  -0.0489   0.0081   1.0000
  13.750   1.4835   0.04242   0.03647  -0.0480   0.0078   1.0000
  14.000   1.4865   0.04468   0.03884  -0.0472   0.0075   1.0000
  14.250   1.4879   0.04716   0.04143  -0.0465   0.0073   1.0000
  14.500   1.4876   0.04996   0.04434  -0.0460   0.0071   1.0000
  14.750   1.4846   0.05322   0.04771  -0.0457   0.0070   1.0000
  15.000   1.4769   0.05720   0.05183  -0.0456   0.0067   1.0000
  15.250   1.4705   0.06122   0.05598  -0.0459   0.0066   1.0000
  15.500   1.4716   0.06437   0.05926  -0.0463   0.0065   1.0000
  15.750   1.4689   0.06817   0.06320  -0.0469   0.0064   1.0000
  16.000   1.4673   0.07194   0.06714  -0.0478   0.0062   1.0000
  16.250   1.4618   0.07646   0.07180  -0.0490   0.0061   1.0000
  16.500   1.4565   0.08112   0.07661  -0.0505   0.0060   1.0000
  16.750   1.4500   0.08613   0.08176  -0.0523   0.0058   1.0000
  17.000   1.4411   0.09173   0.08751  -0.0545   0.0057   1.0000
  17.250   1.4320   0.09758   0.09351  -0.0570   0.0056   1.0000
  17.500   1.4222   0.10372   0.09980  -0.0599   0.0055   1.0000
  17.750   1.4108   0.11032   0.10654  -0.0631   0.0055   1.0000
  18.000   1.3999   0.11699   0.11335  -0.0665   0.0054   1.0000
  18.250   1.3884   0.12393   0.12043  -0.0702   0.0053   1.0000
  18.500   1.3768   0.13100   0.12764  -0.0741   0.0053   1.0000
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