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EPPLER 68 AIRFOIL (e68-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 68 AIRFOIL (e68-il)
Reynolds number: 100,000
Max Cl/Cd: 56.54 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e68-il-100000-n5.txt
Download as CSV file: xf-e68-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 68 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4439   0.09165   0.08678  -0.0539   1.0000   0.0277
 -10.250  -0.4691   0.08463   0.07985  -0.0553   1.0000   0.0272
 -10.000  -0.5247   0.07198   0.06726  -0.0607   1.0000   0.0262
  -9.750  -0.5853   0.06323   0.05846  -0.0643   1.0000   0.0254
  -9.500  -0.6214   0.05583   0.05072  -0.0708   0.9917   0.0249
  -9.250  -0.6233   0.05000   0.04443  -0.0759   0.9835   0.0250
  -9.000  -0.6192   0.04577   0.03979  -0.0777   0.9754   0.0252
  -8.750  -0.6056   0.04212   0.03571  -0.0796   0.9700   0.0256
  -8.500  -0.5921   0.03920   0.03239  -0.0801   0.9634   0.0261
  -8.250  -0.5697   0.03643   0.02921  -0.0816   0.9593   0.0268
  -8.000  -0.5517   0.03425   0.02669  -0.0814   0.9535   0.0276
  -7.750  -0.5283   0.03220   0.02431  -0.0819   0.9487   0.0286
  -7.500  -0.4994   0.03046   0.02220  -0.0831   0.9455   0.0302
  -7.250  -0.4794   0.02918   0.02089  -0.0828   0.9397   0.0323
  -7.000  -0.4533   0.02806   0.01964  -0.0834   0.9350   0.0349
  -6.750  -0.4230   0.02674   0.01809  -0.0844   0.9318   0.0378
  -6.500  -0.4008   0.02558   0.01685  -0.0841   0.9264   0.0408
  -6.250  -0.3753   0.02461   0.01579  -0.0843   0.9213   0.0460
  -6.000  -0.3445   0.02362   0.01475  -0.0856   0.9180   0.0558
  -5.750  -0.3170   0.02282   0.01389  -0.0861   0.9136   0.0703
  -5.500  -0.2931   0.02218   0.01327  -0.0859   0.9075   0.0880
  -5.250  -0.2614   0.02157   0.01269  -0.0872   0.9041   0.1140
  -5.000  -0.2268   0.02091   0.01207  -0.0890   0.9016   0.1412
  -4.750  -0.2078   0.02051   0.01172  -0.0877   0.8939   0.1632
  -4.500  -0.1762   0.02000   0.01124  -0.0888   0.8901   0.1935
  -4.250  -0.1413   0.01949   0.01078  -0.0905   0.8875   0.2303
  -4.000  -0.1202   0.01920   0.01058  -0.0895   0.8804   0.2638
  -3.750  -0.0896   0.01881   0.01027  -0.0903   0.8762   0.3064
  -3.500  -0.0550   0.01841   0.00997  -0.0918   0.8734   0.3533
  -3.250  -0.0316   0.01822   0.00987  -0.0911   0.8668   0.3938
  -3.000  -0.0026   0.01798   0.00970  -0.0913   0.8619   0.4367
  -2.750   0.0319   0.01771   0.00950  -0.0925   0.8588   0.4808
  -2.500   0.0556   0.01763   0.00947  -0.0917   0.8523   0.5176
  -2.250   0.0838   0.01748   0.00937  -0.0916   0.8471   0.5538
  -2.000   0.1176   0.01727   0.00919  -0.0925   0.8439   0.5904
  -1.750   0.1392   0.01727   0.00924  -0.0911   0.8366   0.6212
  -1.500   0.1682   0.01715   0.00915  -0.0910   0.8316   0.6531
  -1.250   0.2017   0.01697   0.00898  -0.0917   0.8284   0.6846
  -1.000   0.2200   0.01705   0.00910  -0.0896   0.8199   0.7109
  -0.750   0.2505   0.01691   0.00898  -0.0897   0.8156   0.7393
  -0.500   0.2751   0.01689   0.00897  -0.0887   0.8094   0.7663
  -0.250   0.2992   0.01686   0.00895  -0.0876   0.8028   0.7926
   0.000   0.3309   0.01668   0.00877  -0.0877   0.7991   0.8183
   0.250   0.3477   0.01677   0.00889  -0.0852   0.7902   0.8444
   0.500   0.3782   0.01660   0.00872  -0.0852   0.7856   0.8708
   0.750   0.4011   0.01662   0.00875  -0.0839   0.7779   0.8983
   1.000   0.4364   0.01649   0.00862  -0.0851   0.7724   0.9249
   1.250   0.4803   0.01635   0.00846  -0.0881   0.7677   0.9494
   1.500   0.5215   0.01636   0.00848  -0.0911   0.7597   0.9777
   1.750   0.5667   0.01618   0.00825  -0.0946   0.7549   1.0000
   2.000   0.5837   0.01633   0.00837  -0.0929   0.7450   1.0000
   2.250   0.6177   0.01622   0.00821  -0.0940   0.7393   1.0000
   2.500   0.6377   0.01638   0.00836  -0.0928   0.7292   1.0000
   2.750   0.6659   0.01640   0.00836  -0.0929   0.7212   1.0000
   3.000   0.6938   0.01643   0.00838  -0.0929   0.7126   1.0000
   3.250   0.7181   0.01655   0.00850  -0.0923   0.7026   1.0000
   3.500   0.7498   0.01651   0.00844  -0.0929   0.6944   1.0000
   3.750   0.7737   0.01664   0.00859  -0.0922   0.6835   1.0000
   4.000   0.7983   0.01676   0.00875  -0.0916   0.6726   1.0000
   4.250   0.8257   0.01682   0.00882  -0.0915   0.6619   1.0000
   4.500   0.8548   0.01685   0.00885  -0.0916   0.6511   1.0000
   4.750   0.8779   0.01701   0.00906  -0.0907   0.6381   1.0000
   5.000   0.9017   0.01716   0.00925  -0.0898   0.6247   1.0000
   5.250   0.9256   0.01732   0.00943  -0.0891   0.6109   1.0000
   5.500   0.9494   0.01748   0.00962  -0.0882   0.5963   1.0000
   5.750   0.9728   0.01766   0.00984  -0.0873   0.5806   1.0000
   6.000   0.9957   0.01785   0.01005  -0.0863   0.5640   1.0000
   6.250   1.0171   0.01808   0.01030  -0.0850   0.5462   1.0000
   6.500   1.0363   0.01837   0.01062  -0.0834   0.5269   1.0000
   6.750   1.0556   0.01867   0.01094  -0.0819   0.5065   1.0000
   7.000   1.0734   0.01902   0.01128  -0.0800   0.4846   1.0000
   7.250   1.0895   0.01943   0.01166  -0.0780   0.4611   1.0000
   7.500   1.1032   0.01987   0.01209  -0.0755   0.4366   1.0000
   7.750   1.1157   0.02041   0.01256  -0.0729   0.4107   1.0000
   8.000   1.1268   0.02103   0.01314  -0.0702   0.3839   1.0000
   8.250   1.1366   0.02175   0.01378  -0.0674   0.3558   1.0000
   8.500   1.1450   0.02258   0.01452  -0.0645   0.3268   1.0000
   8.750   1.1526   0.02350   0.01535  -0.0617   0.2984   1.0000
   9.000   1.1595   0.02453   0.01629  -0.0589   0.2707   1.0000
   9.250   1.1662   0.02563   0.01732  -0.0563   0.2447   1.0000
   9.500   1.1720   0.02684   0.01847  -0.0538   0.2201   1.0000
   9.750   1.1775   0.02814   0.01970  -0.0513   0.1974   1.0000
  10.000   1.1833   0.02950   0.02102  -0.0491   0.1756   1.0000
  10.250   1.1877   0.03100   0.02246  -0.0468   0.1554   1.0000
  10.500   1.1920   0.03259   0.02398  -0.0448   0.1355   1.0000
  10.750   1.1955   0.03431   0.02563  -0.0428   0.1163   1.0000
  11.000   1.1981   0.03616   0.02740  -0.0410   0.1000   1.0000
  11.250   1.2018   0.03801   0.02923  -0.0394   0.0858   1.0000
  11.500   1.2046   0.04000   0.03120  -0.0378   0.0743   1.0000
  11.750   1.2080   0.04201   0.03330  -0.0364   0.0644   1.0000
  12.000   1.2105   0.04417   0.03553  -0.0351   0.0565   1.0000
  12.250   1.2096   0.04672   0.03809  -0.0339   0.0508   1.0000
  12.500   1.2112   0.04913   0.04063  -0.0328   0.0453   1.0000
  12.750   1.2078   0.05211   0.04360  -0.0319   0.0415   1.0000
  13.000   1.2093   0.05470   0.04637  -0.0311   0.0376   1.0000
  13.250   1.2085   0.05761   0.04938  -0.0306   0.0347   1.0000
  13.750   1.2049   0.06397   0.05597  -0.0300   0.0310   1.0000
  14.000   1.2047   0.06713   0.05929  -0.0298   0.0294   1.0000
  14.250   1.2044   0.07037   0.06267  -0.0298   0.0282   1.0000
  14.500   1.2036   0.07376   0.06620  -0.0300   0.0271   1.0000
  14.750   1.2021   0.07729   0.06982  -0.0304   0.0262   1.0000
  15.000   1.2007   0.08086   0.07346  -0.0308   0.0254   1.0000
  15.250   1.2011   0.08439   0.07720  -0.0313   0.0245   1.0000
  15.500   1.2003   0.08819   0.08122  -0.0320   0.0236   1.0000
  15.750   1.1978   0.09231   0.08553  -0.0331   0.0227   1.0000
  16.000   1.1944   0.09664   0.09004  -0.0345   0.0220   1.0000
  16.250   1.1903   0.10117   0.09474  -0.0361   0.0214   1.0000
  16.500   1.1857   0.10587   0.09960  -0.0379   0.0210   1.0000
  16.750   1.1806   0.11076   0.10465  -0.0400   0.0206   1.0000
  17.000   1.1747   0.11589   0.10994  -0.0423   0.0203   1.0000
  17.250   1.1682   0.12129   0.11550  -0.0449   0.0201   1.0000
  17.500   1.1607   0.12700   0.12136  -0.0479   0.0198   1.0000
  17.750   1.1515   0.13324   0.12777  -0.0514   0.0197   1.0000
  18.000   1.1401   0.14025   0.13496  -0.0556   0.0196   1.0000
  18.250   1.1252   0.14845   0.14336  -0.0608   0.0196   1.0000
  18.500   1.0997   0.16018   0.15536  -0.0686   0.0199   1.0000
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