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EPPLER 668 AIRFOIL (e668-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 668 AIRFOIL (e668-il)
Reynolds number: 50,000
Max Cl/Cd: 31 at α=10.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e668-il-50000.txt
Download as CSV file: xf-e668-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 668 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
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.3836   0.11051   0.10549  -0.0087   1.0000   0.3010
  -6.750  -0.3881   0.10761   0.10265  -0.0071   1.0000   0.3104
  -6.500  -0.4232   0.10660   0.10175  -0.0050   1.0000   0.3211
  -6.250  -0.4016   0.10244   0.09758  -0.0033   1.0000   0.3335
  -6.000  -0.4077   0.09950   0.09471  -0.0014   1.0000   0.3433
  -5.750  -0.4288   0.09735   0.09265   0.0013   1.0000   0.3562
  -5.500  -0.4577   0.09599   0.09139   0.0050   1.0000   0.3705
  -5.000  -0.5529   0.06430   0.05782  -0.0378   1.0000   0.1267
  -4.750  -0.5302   0.05735   0.04999  -0.0414   1.0000   0.1130
  -4.500  -0.5095   0.05327   0.04551  -0.0423   1.0000   0.1120
  -4.250  -0.4853   0.04936   0.04103  -0.0435   1.0000   0.1118
  -4.000  -0.4594   0.04597   0.03705  -0.0442   1.0000   0.1117
  -3.750  -0.4329   0.04310   0.03359  -0.0447   1.0000   0.1159
  -3.500  -0.4094   0.04112   0.03145  -0.0445   1.0000   0.1237
  -3.250  -0.3839   0.03921   0.02918  -0.0444   1.0000   0.1337
  -3.000  -0.3592   0.03770   0.02743  -0.0440   1.0000   0.1477
  -2.750  -0.3358   0.03646   0.02619  -0.0433   1.0000   0.1680
  -2.500  -0.3130   0.03535   0.02515  -0.0423   1.0000   0.1988
  -2.250  -0.2902   0.03424   0.02427  -0.0412   1.0000   0.2569
  -2.000  -0.2634   0.03189   0.02380  -0.0409   1.0000   0.4824
  -1.750  -0.2809   0.03172   0.02512  -0.0276   1.0000   0.7711
  -1.500  -0.2936   0.03184   0.02524  -0.0166   1.0000   0.8969
  -1.250  -0.2430   0.03186   0.02472  -0.0208   1.0000   1.0000
  -1.000  -0.2287   0.03181   0.02428  -0.0204   1.0000   1.0000
  -0.750  -0.2109   0.03200   0.02411  -0.0205   1.0000   1.0000
  -0.500  -0.1912   0.03235   0.02413  -0.0209   1.0000   1.0000
  -0.250  -0.1706   0.03282   0.02427  -0.0214   1.0000   1.0000
   0.000  -0.1495   0.03338   0.02455  -0.0220   1.0000   1.0000
   0.250  -0.1283   0.03401   0.02493  -0.0226   1.0000   1.0000
   0.500  -0.1071   0.03471   0.02539  -0.0232   1.0000   1.0000
   0.750  -0.0860   0.03547   0.02594  -0.0238   1.0000   1.0000
   1.000  -0.0651   0.03629   0.02656  -0.0244   1.0000   1.0000
   1.250  -0.0445   0.03716   0.02726  -0.0251   1.0000   1.0000
   1.500  -0.0241   0.03808   0.02801  -0.0257   1.0000   1.0000
   1.750  -0.0041   0.03905   0.02884  -0.0262   1.0000   1.0000
   2.000   0.0156   0.04008   0.02974  -0.0268   1.0000   1.0000
   2.250   0.0350   0.04116   0.03070  -0.0274   1.0000   1.0000
   2.500   0.0540   0.04229   0.03173  -0.0280   1.0000   1.0000
   2.750   0.0727   0.04348   0.03283  -0.0286   1.0000   1.0000
   3.000   0.0910   0.04472   0.03400  -0.0292   1.0000   1.0000
   3.250   0.1090   0.04601   0.03522  -0.0298   1.0000   1.0000
   3.500   0.1266   0.04737   0.03653  -0.0304   1.0000   1.0000
   3.750   0.1616   0.04994   0.03904  -0.0344   0.9905   1.0000
   4.000   0.1979   0.05258   0.04163  -0.0386   0.9762   1.0000
   4.250   0.2346   0.05523   0.04426  -0.0427   0.9604   1.0000
   4.500   0.2724   0.05812   0.04713  -0.0469   0.9441   1.0000
   4.750   0.2980   0.05990   0.04893  -0.0490   0.9262   1.0000
   5.000   0.3258   0.06168   0.05073  -0.0512   0.9043   1.0000
   5.250   0.3713   0.06481   0.05387  -0.0558   0.8820   1.0000
   5.500   0.4504   0.06423   0.05331  -0.0603   0.7932   1.0000
   5.750   0.4892   0.06520   0.05432  -0.0622   0.7686   1.0000
   6.000   0.5149   0.06619   0.05537  -0.0628   0.7495   1.0000
   6.250   0.5466   0.06720   0.05647  -0.0641   0.7318   1.0000
   6.500   0.5822   0.06810   0.05747  -0.0656   0.7150   1.0000
   6.750   0.6177   0.06890   0.05836  -0.0669   0.6988   1.0000
   7.000   0.6340   0.06998   0.05956  -0.0665   0.6815   1.0000
   7.250   0.6567   0.07099   0.06067  -0.0667   0.6648   1.0000
   7.500   0.6815   0.07192   0.06172  -0.0670   0.6481   1.0000
   7.750   0.7078   0.07272   0.06267  -0.0672   0.6314   1.0000
   8.000   0.7348   0.07344   0.06353  -0.0674   0.6149   1.0000
   8.250   0.7632   0.07393   0.06418  -0.0675   0.5983   1.0000
   8.500   0.7932   0.07420   0.06464  -0.0674   0.5817   1.0000
   8.750   0.8254   0.07413   0.06476  -0.0673   0.5650   1.0000
   9.000   0.8610   0.07354   0.06438  -0.0669   0.5484   1.0000
   9.250   0.9014   0.07216   0.06326  -0.0663   0.5319   1.0000
   9.500   0.9490   0.06955   0.06093  -0.0654   0.5155   1.0000
   9.750   1.0098   0.06459   0.05633  -0.0638   0.4997   1.0000
  10.000   0.9842   0.07024   0.06202  -0.0621   0.4757   1.0000
  10.250   1.2489   0.04289   0.03540  -0.0647   0.4330   1.0000
  10.500   1.2913   0.04166   0.03397  -0.0640   0.3880   1.0000
  10.750   1.3017   0.04271   0.03492  -0.0612   0.3537   1.0000
  11.000   1.3118   0.04400   0.03608  -0.0586   0.3205   1.0000
  11.250   1.3208   0.04556   0.03748  -0.0561   0.2899   1.0000
  11.500   1.3305   0.04733   0.03908  -0.0538   0.2613   1.0000
  11.750   1.3445   0.04920   0.04072  -0.0522   0.2338   1.0000
  12.000   1.3449   0.05166   0.04328  -0.0495   0.2147   1.0000
  12.250   1.3517   0.05404   0.04568  -0.0475   0.1957   1.0000
  12.500   1.3733   0.05648   0.04791  -0.0469   0.1747   1.0000
  12.750   1.3828   0.05935   0.05084  -0.0454   0.1604   1.0000
  13.000   1.3684   0.06267   0.05460  -0.0422   0.1539   1.0000
  13.250   1.3750   0.06593   0.05796  -0.0408   0.1436   1.0000
  13.500   1.3913   0.06914   0.06113  -0.0402   0.1323   1.0000
  13.750   1.3678   0.07325   0.06570  -0.0372   0.1305   1.0000
  14.000   1.3442   0.07785   0.07068  -0.0349   0.1288   1.0000
  14.250   1.3186   0.08292   0.07609  -0.0334   0.1276   1.0000
  14.500   1.2893   0.08873   0.08221  -0.0326   0.1276   1.0000
  14.750   1.2547   0.09553   0.08929  -0.0329   0.1286   1.0000
  15.000   1.2193   0.10330   0.09728  -0.0345   0.1301   1.0000
  15.250   1.1849   0.11190   0.10603  -0.0374   0.1316   1.0000
  15.500   1.1533   0.12137   0.11558  -0.0413   0.1327   1.0000
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