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EPPLER 694 AIRFOIL (e694-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 694 AIRFOIL (e694-il)
Reynolds number: 500,000
Max Cl/Cd: 113.14 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e694-il-500000.txt
Download as CSV file: xf-e694-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 694 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500   0.0995   0.09257   0.08989  -0.1645   0.9421   0.0238
 -12.250   0.0148   0.09864   0.09583  -0.1692   0.9505   0.0227
 -12.000   0.0273   0.09522   0.09240  -0.1721   0.9501   0.0228
 -11.750   0.0445   0.09352   0.09069  -0.1737   0.9497   0.0238
 -11.500   0.0559   0.09008   0.08724  -0.1769   0.9492   0.0244
 -11.250   0.0656   0.08588   0.08304  -0.1809   0.9487   0.0260
 -11.000   0.0425   0.08548   0.08269  -0.1737   0.9419   0.0257
 -10.750   0.0360   0.07701   0.07424  -0.1814   0.9397   0.0276
 -10.250   0.1114   0.05842   0.05578  -0.1774   0.9299   0.0306
 -10.000   0.1071   0.05423   0.05160  -0.1787   0.9274   0.0316
  -9.750   0.0958   0.04708   0.04446  -0.1832   0.9253   0.0330
  -9.500   0.0715   0.03705   0.03438  -0.1917   0.9231   0.0324
  -9.250   0.0411   0.03307   0.03034  -0.1918   0.9171   0.0319
  -9.000   0.0128   0.02960   0.02675  -0.1910   0.9109   0.0317
  -8.750  -0.0044   0.02625   0.02322  -0.1911   0.9073   0.0321
  -8.500  -0.0329   0.02572   0.02264  -0.1839   0.8974   0.0322
  -8.250  -0.0407   0.02460   0.02096  -0.1826   0.8934   0.0345
  -8.000  -0.0639   0.03885   0.03489  -0.1858   0.8944   0.0345
  -7.500  -0.0968   0.02241   0.01689  -0.1753   0.8814   0.0183
  -7.250  -0.0660   0.02100   0.01522  -0.1766   0.8802   0.0179
  -7.000  -0.0342   0.01947   0.01350  -0.1780   0.8793   0.0179
  -6.750  -0.0022   0.01796   0.01186  -0.1795   0.8784   0.0183
  -6.500  -0.0079   0.01763   0.01151  -0.1730   0.8700   0.0184
  -6.250   0.0200   0.01676   0.01058  -0.1735   0.8680   0.0187
  -6.000   0.0502   0.01599   0.00977  -0.1746   0.8666   0.0193
  -5.750   0.0825   0.01528   0.00901  -0.1760   0.8654   0.0198
  -5.500   0.1167   0.01471   0.00837  -0.1779   0.8644   0.0210
  -5.250   0.1517   0.01419   0.00779  -0.1799   0.8635   0.0220
  -5.000   0.1478   0.01407   0.00767  -0.1737   0.8558   0.0224
  -4.750   0.1760   0.01348   0.00704  -0.1744   0.8538   0.0239
  -4.500   0.2076   0.01308   0.00661  -0.1756   0.8524   0.0262
  -4.250   0.2413   0.01266   0.00616  -0.1773   0.8513   0.0309
  -4.000   0.2767   0.01196   0.00571  -0.1797   0.8503   0.0848
  -3.750   0.3129   0.01139   0.00543  -0.1823   0.8494   0.1651
  -3.500   0.3506   0.01073   0.00517  -0.1855   0.8486   0.2852
  -3.250   0.3544   0.01064   0.00540  -0.1813   0.8425   0.3683
  -3.000   0.3892   0.01009   0.00531  -0.1838   0.8409   0.5133
  -2.750   0.4226   0.00976   0.00531  -0.1855   0.8395   0.6180
  -2.500   0.4530   0.00969   0.00541  -0.1861   0.8381   0.6823
  -2.250   0.4849   0.00972   0.00545  -0.1871   0.8369   0.7096
  -2.000   0.5182   0.00979   0.00547  -0.1883   0.8359   0.7317
  -1.750   0.5528   0.00985   0.00547  -0.1898   0.8350   0.7460
  -1.500   0.5602   0.01018   0.00584  -0.1855   0.8304   0.7536
  -1.250   0.5808   0.01036   0.00601  -0.1841   0.8274   0.7639
  -1.000   0.6048   0.01051   0.00616  -0.1832   0.8254   0.7722
  -0.750   0.6334   0.01062   0.00624  -0.1833   0.8240   0.7812
  -0.500   0.6635   0.01068   0.00629  -0.1838   0.8227   0.7872
  -0.250   0.7004   0.01066   0.00622  -0.1860   0.8217   0.7938
   0.000   0.7230   0.01074   0.00631  -0.1849   0.8194   0.7970
   0.250   0.7236   0.01098   0.00658  -0.1792   0.8140   0.8016
   0.500   0.7531   0.01095   0.00654  -0.1798   0.8118   0.8067
   0.750   0.7878   0.01089   0.00645  -0.1814   0.8103   0.8109
   1.000   0.8209   0.01083   0.00639  -0.1825   0.8087   0.8142
   1.250   0.8529   0.01081   0.00636  -0.1834   0.8067   0.8186
   1.500   0.8577   0.01100   0.00657  -0.1789   0.8012   0.8251
   1.750   0.8862   0.01087   0.00644  -0.1791   0.7981   0.8276
   2.000   0.9269   0.01064   0.00618  -0.1818   0.7951   0.8297
   2.250   0.9446   0.01068   0.00624  -0.1798   0.7902   0.8330
   2.500   0.9704   0.01067   0.00624  -0.1796   0.7858   0.8364
   2.750   1.0081   0.01064   0.00618  -0.1821   0.7831   0.8392
   3.000   1.0513   0.01060   0.00613  -0.1857   0.7805   0.8410
   3.250   1.0622   0.01069   0.00627  -0.1823   0.7753   0.8435
   3.500   1.0881   0.01072   0.00632  -0.1821   0.7708   0.8458
   3.750   1.1262   0.01073   0.00634  -0.1845   0.7673   0.8478
   4.000   1.1569   0.01082   0.00645  -0.1855   0.7631   0.8501
   4.250   1.1734   0.01093   0.00659  -0.1834   0.7573   0.8533
   4.500   1.2142   0.01096   0.00660  -0.1865   0.7516   0.8550
   4.750   1.2234   0.01103   0.00673  -0.1827   0.7443   0.8574
   5.000   1.2466   0.01105   0.00677  -0.1819   0.7371   0.8595
   5.250   1.2627   0.01118   0.00693  -0.1796   0.7301   0.8624
   5.500   1.2773   0.01129   0.00709  -0.1771   0.7222   0.8656
   5.750   1.2918   0.01146   0.00730  -0.1747   0.7138   0.8688
   6.000   1.3045   0.01155   0.00743  -0.1718   0.7042   0.8711
   6.250   1.3046   0.01183   0.00779  -0.1664   0.6922   0.8738
   6.500   1.3085   0.01212   0.00812  -0.1620   0.6759   0.8762
   6.750   1.3133   0.01251   0.00849  -0.1578   0.6534   0.8790
   7.000   1.3178   0.01307   0.00890  -0.1536   0.6208   0.8814
   7.250   1.3174   0.01401   0.00960  -0.1487   0.5786   0.8835
   7.500   1.3156   0.01506   0.01045  -0.1438   0.5396   0.8853
   7.750   1.3143   0.01616   0.01139  -0.1391   0.5037   0.8874
   8.000   1.3127   0.01739   0.01245  -0.1345   0.4668   0.8897
   8.500   1.3145   0.02002   0.01476  -0.1268   0.3947   0.8937
   8.750   1.3164   0.02145   0.01600  -0.1234   0.3570   0.8955
   9.000   1.3211   0.02283   0.01721  -0.1206   0.3227   0.8971
   9.250   1.3273   0.02415   0.01839  -0.1180   0.2899   0.8986
   9.500   1.3307   0.02561   0.01967  -0.1151   0.2536   0.9004
   9.750   1.3370   0.02695   0.02090  -0.1126   0.2283   0.9023
  10.000   1.3449   0.02828   0.02210  -0.1105   0.1996   0.9042
  10.250   1.3505   0.02983   0.02347  -0.1083   0.1643   0.9059
  10.500   1.3572   0.03139   0.02486  -0.1063   0.1353   0.9076
  10.750   1.3621   0.03314   0.02644  -0.1042   0.1050   0.9092
  11.000   1.3674   0.03494   0.02806  -0.1022   0.0769   0.9107
  11.250   1.3685   0.03714   0.03004  -0.0999   0.0450   0.9121
  11.500   1.3686   0.03942   0.03217  -0.0975   0.0230   0.9136
  11.750   1.3764   0.04110   0.03385  -0.0959   0.0182   0.9154
  12.000   1.3868   0.04259   0.03541  -0.0946   0.0164   0.9173
  12.250   1.3958   0.04423   0.03711  -0.0933   0.0151   0.9195
  12.500   1.4027   0.04613   0.03910  -0.0919   0.0142   0.9217
  12.750   1.4122   0.04784   0.04091  -0.0908   0.0137   0.9239
  13.000   1.4202   0.04972   0.04288  -0.0896   0.0133   0.9259
  13.250   1.4271   0.05162   0.04488  -0.0884   0.0128   0.9282
  13.500   1.4331   0.05367   0.04703  -0.0872   0.0124   0.9306
  13.750   1.4377   0.05594   0.04938  -0.0861   0.0120   0.9330
  14.000   1.4394   0.05862   0.05216  -0.0849   0.0116   0.9354
  14.250   1.4376   0.06180   0.05544  -0.0836   0.0113   0.9377
  14.500   1.4366   0.06486   0.05862  -0.0825   0.0111   0.9403
  14.750   1.4399   0.06744   0.06131  -0.0816   0.0109   0.9438
  15.000   1.4424   0.07016   0.06415  -0.0809   0.0108   0.9479
  15.250   1.4442   0.07294   0.06705  -0.0801   0.0107   0.9535
  15.750   1.4457   0.07874   0.07309  -0.0789   0.0104   1.0000
  16.000   1.4485   0.08191   0.07636  -0.0789   0.0102   1.0000
  16.250   1.4511   0.08513   0.07969  -0.0790   0.0101   1.0000
  16.500   1.4535   0.08840   0.08305  -0.0791   0.0100   1.0000
  16.750   1.4564   0.09163   0.08640  -0.0794   0.0098   1.0000
  17.000   1.4589   0.09493   0.08980  -0.0797   0.0097   1.0000
  17.250   1.4615   0.09824   0.09323  -0.0802   0.0096   1.0000
  17.500   1.4640   0.10155   0.09665  -0.0807   0.0095   1.0000
  17.750   1.4661   0.10494   0.10015  -0.0813   0.0094   1.0000
  18.000   1.4681   0.10834   0.10367  -0.0820   0.0093   1.0000
  18.250   1.4697   0.11183   0.10727  -0.0829   0.0092   1.0000
  18.500   1.4707   0.11542   0.11096  -0.0839   0.0091   1.0000
  18.750   1.4716   0.11900   0.11464  -0.0850   0.0090   1.0000
  19.000   1.4723   0.12257   0.11831  -0.0862   0.0088   1.0000
  19.250   1.4726   0.12615   0.12201  -0.0874   0.0087   1.0000
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