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EPPLER 342 AIRFOIL (e342-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 342 AIRFOIL (e342-il)
Reynolds number: 50,000
Max Cl/Cd: 14.62 at α=0.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e342-il-50000.txt
Download as CSV file: xf-e342-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 342 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3650   0.11890   0.11263  -0.0148   1.0000   0.2165
  -9.750  -0.3378   0.11365   0.10740  -0.0132   1.0000   0.2269
  -9.500  -0.3749   0.11347   0.10741  -0.0164   1.0000   0.2347
  -9.250  -0.3432   0.10834   0.10229  -0.0142   1.0000   0.2500
  -9.000  -0.3305   0.10449   0.09852  -0.0133   1.0000   0.2645
  -8.750  -0.3241   0.10127   0.09539  -0.0128   1.0000   0.2788
  -8.500  -0.3201   0.09831   0.09254  -0.0121   1.0000   0.2960
  -8.250  -0.3187   0.09563   0.08997  -0.0111   1.0000   0.3169
  -8.000  -0.3342   0.09394   0.08845  -0.0102   1.0000   0.3382
  -7.750  -0.3013   0.08994   0.08449  -0.0078   1.0000   0.3665
  -7.500  -0.2903   0.08725   0.08193  -0.0055   1.0000   0.3991
  -7.250  -0.2847   0.08533   0.08014  -0.0023   1.0000   0.4408
  -7.000  -0.2454   0.08208   0.07695   0.0014   1.0000   0.5054
  -6.750  -0.2322   0.08064   0.07565   0.0053   1.0000   0.5639
  -6.500  -0.1811   0.07646   0.07155   0.0056   1.0000   0.6279
  -5.250  -0.3479   0.05793   0.05341  -0.0251   0.9130   0.3858
  -5.000  -0.3351   0.05087   0.04402  -0.0356   0.8922   0.1621
  -4.750  -0.2964   0.04727   0.03938  -0.0363   0.8788   0.1307
  -4.500  -0.2655   0.04390   0.03576  -0.0368   0.8631   0.1262
  -4.250  -0.2378   0.04149   0.03280  -0.0360   0.8478   0.1200
  -4.000  -0.2081   0.03997   0.03053  -0.0348   0.8328   0.1149
  -3.750  -0.1737   0.03776   0.02801  -0.0351   0.8190   0.1138
  -3.500   0.2259   0.02646   0.01894  -0.0819   0.8035   1.0000
  -3.250   0.2450   0.02663   0.01868  -0.0809   0.7870   1.0000
  -3.000   0.2640   0.02683   0.01852  -0.0798   0.7723   1.0000
  -2.750   0.2828   0.02707   0.01846  -0.0787   0.7589   1.0000
  -2.500   0.3021   0.02742   0.01856  -0.0781   0.7456   1.0000
  -2.250   0.3218   0.02779   0.01869  -0.0773   0.7339   1.0000
  -2.000   0.3413   0.02812   0.01876  -0.0762   0.7237   1.0000
  -1.750   0.3600   0.02869   0.01919  -0.0757   0.7128   1.0000
  -1.500   0.3794   0.02909   0.01935  -0.0745   0.7043   1.0000
  -1.250   0.3975   0.02978   0.01994  -0.0740   0.6939   1.0000
  -1.000   0.4167   0.03028   0.02025  -0.0728   0.6861   1.0000
  -0.750   0.4341   0.03116   0.02106  -0.0724   0.6770   1.0000
  -0.500   0.4541   0.03163   0.02135  -0.0711   0.6706   1.0000
  -0.250   0.4692   0.03283   0.02254  -0.0708   0.6619   1.0000
   0.000   0.4877   0.03351   0.02309  -0.0696   0.6551   1.0000
   0.250   0.5029   0.03469   0.02423  -0.0689   0.6484   1.0000
   0.500   0.5165   0.03599   0.02550  -0.0681   0.6415   1.0000
   0.750   0.5358   0.03666   0.02605  -0.0668   0.6361   1.0000
   1.000   0.5421   0.03866   0.02809  -0.0659   0.6293   1.0000
   1.250   0.5512   0.04028   0.02970  -0.0647   0.6234   1.0000
   1.500   0.5698   0.04115   0.03047  -0.0634   0.6187   1.0000
   1.750   0.5665   0.04379   0.03316  -0.0617   0.6136   1.0000
   2.000   0.5568   0.04664   0.03604  -0.0593   0.6085   1.0000
   2.250   0.5587   0.04864   0.03803  -0.0573   0.6043   1.0000
   2.500   0.5820   0.04944   0.03875  -0.0563   0.6003   1.0000
   2.750   0.5523   0.05335   0.04269  -0.0525   0.5981   1.0000
   3.000   0.5201   0.05694   0.04629  -0.0480   0.5976   1.0000
   3.250   0.4940   0.05985   0.04917  -0.0434   0.5985   1.0000
   3.500   0.4839   0.06235   0.05165  -0.0405   0.6001   1.0000
   3.750   0.2406   0.07156   0.06117  -0.0261   0.7926   1.0000
   4.000   0.2442   0.07226   0.06180  -0.0237   0.7777   1.0000
   4.250   0.2503   0.07343   0.06291  -0.0218   0.7642   1.0000
   4.500   0.2648   0.07531   0.06472  -0.0212   0.7533   1.0000
   4.750   0.2920   0.07786   0.06721  -0.0222   0.7410   1.0000
   5.000   0.2905   0.07845   0.06776  -0.0193   0.7271   1.0000
   5.250   0.2976   0.08000   0.06925  -0.0178   0.7161   1.0000
   5.500   0.3277   0.08298   0.07220  -0.0191   0.7059   1.0000
   5.750   0.3247   0.08351   0.07270  -0.0162   0.6917   1.0000
   6.000   0.3298   0.08510   0.07425  -0.0146   0.6817   1.0000
   6.250   0.3541   0.08772   0.07685  -0.0151   0.6716   1.0000
   6.500   0.3494   0.08844   0.07753  -0.0123   0.6592   1.0000
   6.750   0.3775   0.09193   0.08101  -0.0134   0.6518   1.0000
   7.000   0.3745   0.09239   0.08146  -0.0108   0.6383   1.0000
   7.250   0.3761   0.09394   0.08300  -0.0091   0.6289   1.0000
   7.500   0.3993   0.09669   0.08575  -0.0094   0.6191   1.0000
   7.750   0.3932   0.09749   0.08654  -0.0070   0.6075   1.0000
   8.000   0.4268   0.10160   0.09067  -0.0085   0.6002   1.0000
   8.250   0.4115   0.10144   0.09048  -0.0053   0.5881   1.0000
   8.500   0.4398   0.10548   0.09455  -0.0063   0.5819   1.0000
   8.750   0.4316   0.10564   0.09470  -0.0039   0.5689   1.0000
   9.000   0.4385   0.10802   0.09709  -0.0032   0.5619   1.0000
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