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EPPLER 339 AIRFOIL (e339-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 339 AIRFOIL (e339-il)
Reynolds number: 100,000
Max Cl/Cd: 34.2 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e339-il-100000.txt
Download as CSV file: xf-e339-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 339 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2852   0.09860   0.09424  -0.0362   1.0000   0.0732
  -8.500  -0.3026   0.09609   0.09186  -0.0399   1.0000   0.0740
  -8.250  -0.3255   0.09386   0.08976  -0.0415   1.0000   0.0742
  -8.000  -0.2910   0.08913   0.08507  -0.0366   1.0000   0.0778
  -7.750  -0.2968   0.08658   0.08266  -0.0363   1.0000   0.0790
  -7.500  -0.3692   0.08793   0.08430  -0.0326   0.9995   0.0755
  -7.250  -0.3294   0.08321   0.07962  -0.0350   0.9921   0.0817
  -7.000  -0.3202   0.07899   0.07488  -0.0517   0.9553   0.0865
  -6.750  -0.2790   0.07144   0.06766  -0.0526   0.9489   0.0907
  -6.500  -0.2517   0.06712   0.06316  -0.0591   0.9287   0.0979
  -6.250  -0.2289   0.06195   0.05778  -0.0642   0.9095   0.1033
  -6.000  -0.2067   0.06077   0.05604  -0.0677   0.8872   0.1155
  -5.750  -0.1797   0.05429   0.04972  -0.0696   0.8687   0.1200
  -5.500  -0.1685   0.05305   0.04795  -0.0696   0.8461   0.1335
  -5.250  -0.1465   0.04889   0.04393  -0.0694   0.8262   0.1393
  -5.000  -0.1355   0.04676   0.04152  -0.0682   0.8072   0.1538
  -4.750  -0.1231   0.04478   0.03933  -0.0667   0.7900   0.1707
  -4.500  -0.1092   0.04267   0.03710  -0.0651   0.7746   0.1895
  -4.250  -0.0949   0.04058   0.03495  -0.0632   0.7599   0.2116
  -4.000  -0.0847   0.03884   0.03314  -0.0609   0.7453   0.2448
  -3.750  -0.0728   0.03727   0.03147  -0.0585   0.7321   0.2785
  -3.500  -0.0562   0.03522   0.02938  -0.0563   0.7209   0.3062
  -3.250   0.0136   0.03051   0.02203  -0.0561   0.7112   0.0731
  -3.000   0.0406   0.02849   0.01942  -0.0543   0.7013   0.0634
  -2.750   0.0663   0.02688   0.01759  -0.0534   0.6901   0.0623
  -2.500   0.0925   0.02586   0.01623  -0.0522   0.6795   0.0635
  -2.250   0.1212   0.02455   0.01466  -0.0515   0.6701   0.0646
  -2.000   0.1489   0.02330   0.01339  -0.0510   0.6597   0.0663
  -1.750   0.1776   0.02238   0.01239  -0.0505   0.6516   0.0707
  -1.500   0.4143   0.01820   0.01060  -0.0833   0.6335   1.0000
  -1.250   0.4350   0.01834   0.01056  -0.0823   0.6242   1.0000
  -1.000   0.4569   0.01846   0.01043  -0.0813   0.6168   1.0000
  -0.750   0.4781   0.01867   0.01049  -0.0804   0.6091   1.0000
  -0.500   0.4997   0.01883   0.01048  -0.0795   0.6016   1.0000
  -0.250   0.5220   0.01902   0.01047  -0.0786   0.5954   1.0000
   0.000   0.5426   0.01927   0.01067  -0.0777   0.5875   1.0000
   0.250   0.5652   0.01946   0.01069  -0.0768   0.5817   1.0000
   0.500   0.5866   0.01977   0.01091  -0.0759   0.5757   1.0000
   0.750   0.6076   0.02006   0.01116  -0.0749   0.5689   1.0000
   1.000   0.6304   0.02027   0.01122  -0.0741   0.5636   1.0000
   1.250   0.6511   0.02065   0.01156  -0.0731   0.5578   1.0000
   1.500   0.6716   0.02103   0.01193  -0.0721   0.5518   1.0000
   1.750   0.6942   0.02129   0.01209  -0.0713   0.5469   1.0000
   2.000   0.7156   0.02168   0.01243  -0.0703   0.5421   1.0000
   2.250   0.7340   0.02219   0.01300  -0.0691   0.5358   1.0000
   2.500   0.7554   0.02255   0.01332  -0.0681   0.5310   1.0000
   2.750   0.7789   0.02287   0.01353  -0.0674   0.5272   1.0000
   3.000   0.7943   0.02360   0.01438  -0.0658   0.5212   1.0000
   3.250   0.8135   0.02410   0.01490  -0.0645   0.5160   1.0000
   3.500   0.8355   0.02445   0.01520  -0.0636   0.5119   1.0000
   3.750   0.8556   0.02502   0.01575  -0.0625   0.5078   1.0000
   4.000   0.8679   0.02592   0.01682  -0.0605   0.5018   1.0000
   4.250   0.8875   0.02640   0.01730  -0.0593   0.4972   1.0000
   4.500   0.9104   0.02674   0.01758  -0.0584   0.4936   1.0000
   4.750   0.9220   0.02775   0.01872  -0.0563   0.4886   1.0000
   5.000   0.9330   0.02872   0.01981  -0.0540   0.4830   1.0000
   5.250   0.9540   0.02910   0.02020  -0.0529   0.4789   1.0000
   5.500   0.9788   0.02938   0.02041  -0.0523   0.4755   1.0000
   5.750   0.9756   0.03113   0.02241  -0.0484   0.4693   1.0000
   6.000   0.9867   0.03202   0.02338  -0.0461   0.4642   1.0000
   6.250   1.0121   0.03214   0.02348  -0.0455   0.4605   1.0000
   6.500   1.0277   0.03290   0.02428  -0.0437   0.4565   1.0000
   6.750   1.0085   0.03531   0.02695  -0.0379   0.4496   1.0000
   7.000   1.0278   0.03564   0.02731  -0.0365   0.4453   1.0000
   7.250   1.0630   0.03530   0.02691  -0.0370   0.4421   1.0000
   7.500   1.0132   0.03915   0.03104  -0.0278   0.4347   1.0000
   7.750   1.0136   0.04034   0.03229  -0.0243   0.4295   1.0000
   8.000   1.0634   0.03915   0.03108  -0.0261   0.4264   1.0000
   8.250   0.8414   0.05499   0.04703  -0.0075   0.4104   1.0000
   8.500   0.9207   0.05005   0.04215  -0.0075   0.4103   1.0000
   8.750   1.0347   0.04464   0.03681  -0.0134   0.4097   1.0000
   9.000   0.8266   0.06470   0.05681  -0.0054   0.3905   1.0000
   9.250   0.9026   0.05881   0.05102  -0.0035   0.3910   1.0000
   9.500   0.9823   0.05323   0.04554  -0.0029   0.3908   1.0000
  10.250   0.7418   0.08874   0.08098  -0.0071   0.3492   1.0000
  10.500   0.7839   0.08692   0.07923  -0.0056   0.3451   1.0000
  10.750   0.7495   0.09413   0.08646  -0.0073   0.3357   1.0000
  11.000   0.7813   0.09336   0.08577  -0.0062   0.3302   1.0000
  11.250   0.7658   0.09852   0.09097  -0.0073   0.3222   1.0000
  11.500   0.7815   0.09972   0.09223  -0.0069   0.3158   1.0000
  11.750   0.8336   0.09629   0.08891  -0.0047   0.3129   1.0000
  12.000   0.7857   0.10576   0.09837  -0.0078   0.3016   1.0000
  12.250   0.8352   0.10242   0.09515  -0.0055   0.2982   1.0000
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