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E62 (5.62%) (e62-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E62 (5.62%) (e62-il)
Reynolds number: 50,000
Max Cl/Cd: 47.67 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e62-il-50000-n5.txt
Download as CSV file: xf-e62-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E62  (5.62%)                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -6.750  -0.3550   0.10450   0.09817  -0.0218   1.0000   0.0799
  -6.500  -0.3589   0.10295   0.09672  -0.0217   1.0000   0.0819
  -6.250  -0.3628   0.10197   0.09585  -0.0237   1.0000   0.0836
  -6.000  -0.3613   0.10085   0.09481  -0.0284   1.0000   0.0844
  -5.750  -0.3588   0.09684   0.09089  -0.0262   1.0000   0.0854
  -5.500  -0.3559   0.09333   0.08741  -0.0229   1.0000   0.0873
  -5.250  -0.3520   0.09062   0.08475  -0.0223   1.0000   0.0898
  -5.000  -0.3463   0.08804   0.08221  -0.0234   1.0000   0.0931
  -4.750  -0.3225   0.08601   0.08013  -0.0357   1.0000   0.0984
  -4.500  -0.3179   0.08221   0.07640  -0.0339   1.0000   0.0997
  -4.250  -0.3127   0.07907   0.07330  -0.0318   1.0000   0.1020
  -4.000  -0.2998   0.07613   0.07030  -0.0333   1.0000   0.1060
  -3.750  -0.2644   0.07211   0.06620  -0.0430   0.9981   0.1146
  -3.500  -0.2222   0.06807   0.06203  -0.0523   0.9937   0.1280
  -3.250  -0.1981   0.06462   0.05856  -0.0540   0.9892   0.1362
  -3.000  -0.1082   0.05564   0.04897  -0.0752   0.9874   0.0726
  -2.750  -0.0606   0.05070   0.04376  -0.0822   0.9851   0.0543
  -2.500   0.0166   0.04439   0.03655  -0.0959   0.9844   0.0450
  -2.250   0.0600   0.04078   0.03270  -0.1015   0.9816   0.0436
  -2.000   0.1104   0.03735   0.02869  -0.1078   0.9794   0.0425
  -1.750   0.1597   0.03446   0.02518  -0.1131   0.9772   0.0419
  -1.500   0.2059   0.03217   0.02225  -0.1172   0.9748   0.0422
  -1.250   0.2485   0.03067   0.02007  -0.1202   0.9720   0.0449
  -1.000   0.2840   0.02944   0.01865  -0.1223   0.9673   0.0507
  -0.750   0.3213   0.02854   0.01730  -0.1240   0.9632   0.0549
  -0.500   0.3597   0.02779   0.01624  -0.1259   0.9596   0.0620
  -0.250   0.3942   0.02722   0.01552  -0.1274   0.9538   0.0836
   0.000   0.4293   0.02464   0.01551  -0.1295   0.9522   0.6917
   0.250   0.4556   0.02461   0.01508  -0.1291   0.9427   1.0000
   0.500   0.4913   0.02500   0.01499  -0.1309   0.9364   1.0000
   0.750   0.5210   0.02535   0.01504  -0.1317   0.9280   1.0000
   1.000   0.5582   0.02571   0.01512  -0.1337   0.9222   1.0000
   1.250   0.5862   0.02606   0.01529  -0.1342   0.9128   1.0000
   1.500   0.6180   0.02640   0.01548  -0.1353   0.9048   1.0000
   1.750   0.6526   0.02668   0.01565  -0.1368   0.8971   1.0000
   2.000   0.6814   0.02702   0.01592  -0.1372   0.8873   1.0000
   2.250   0.7149   0.02726   0.01615  -0.1384   0.8789   1.0000
   2.500   0.7483   0.02747   0.01636  -0.1395   0.8700   1.0000
   2.750   0.7772   0.02775   0.01666  -0.1399   0.8592   1.0000
   3.000   0.8089   0.02793   0.01691  -0.1406   0.8491   1.0000
   3.250   0.8478   0.02784   0.01697  -0.1422   0.8409   1.0000
   3.500   0.8773   0.02796   0.01720  -0.1423   0.8287   1.0000
   3.750   0.9082   0.02799   0.01738  -0.1425   0.8163   1.0000
   4.000   0.9403   0.02791   0.01747  -0.1428   0.8037   1.0000
   4.250   0.9737   0.02772   0.01756  -0.1430   0.7903   1.0000
   4.500   1.0081   0.02742   0.01750  -0.1433   0.7757   1.0000
   4.750   1.0442   0.02700   0.01735  -0.1436   0.7598   1.0000
   5.000   1.0781   0.02660   0.01731  -0.1434   0.7410   1.0000
   5.250   1.1090   0.02624   0.01723  -0.1426   0.7180   1.0000
   5.500   1.1383   0.02589   0.01718  -0.1415   0.6904   1.0000
   5.750   1.1661   0.02561   0.01717  -0.1399   0.6563   1.0000
   6.000   1.1913   0.02547   0.01725  -0.1379   0.6126   1.0000
   6.250   1.2147   0.02548   0.01744  -0.1356   0.5544   1.0000
   6.500   1.2336   0.02595   0.01763  -0.1324   0.4657   1.0000
   6.750   1.2362   0.02768   0.01845  -0.1276   0.3404   1.0000
   7.000   1.2309   0.03033   0.02002  -0.1230   0.2127   1.0000
   7.250   1.2303   0.03336   0.02204  -0.1198   0.1036   1.0000
   7.500   1.2370   0.03615   0.02449  -0.1170   0.0621   1.0000
   7.750   1.2463   0.03860   0.02699  -0.1143   0.0494   1.0000
   8.000   1.2562   0.04092   0.02942  -0.1119   0.0435   1.0000
   8.250   1.2697   0.04316   0.03203  -0.1096   0.0398   1.0000
   8.500   1.2855   0.04535   0.03449  -0.1079   0.0357   1.0000
   8.750   1.2999   0.04791   0.03713  -0.1063   0.0323   1.0000
   9.000   1.3249   0.05067   0.04025  -0.1056   0.0300   1.0000
   9.250   1.3529   0.05408   0.04412  -0.1052   0.0288   1.0000
   9.500   1.3734   0.05790   0.04844  -0.1042   0.0281   1.0000
   9.750   1.3842   0.06181   0.05285  -0.1023   0.0277   1.0000
  10.000   1.3869   0.06575   0.05725  -0.0996   0.0274   1.0000
  10.250   1.3831   0.06972   0.06165  -0.0967   0.0273   1.0000
  10.500   1.3744   0.07379   0.06612  -0.0937   0.0273   1.0000
  10.750   1.3619   0.07803   0.07074  -0.0911   0.0273   1.0000
  11.000   1.3463   0.08261   0.07565  -0.0891   0.0274   1.0000
  11.250   1.3286   0.08755   0.08090  -0.0880   0.0275   1.0000
  11.500   1.3095   0.09293   0.08656  -0.0879   0.0276   1.0000
  11.750   1.2892   0.09886   0.09275  -0.0890   0.0278   1.0000
  12.000   1.2683   0.10546   0.09957  -0.0913   0.0280   1.0000
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