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EPPLER 59 AIRFOIL (e59-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 59 AIRFOIL (e59-il)
Reynolds number: 500,000
Max Cl/Cd: 155.56 at α=1.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e59-il-500000.txt
Download as CSV file: xf-e59-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 59 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4177   0.11875   0.11650  -0.0158   1.0000   0.0132
  -9.000  -0.4166   0.11636   0.11414  -0.0154   1.0000   0.0134
  -8.750  -0.4160   0.11399   0.11178  -0.0149   1.0000   0.0137
  -8.500  -0.4054   0.11060   0.10840  -0.0175   0.9989   0.0142
  -8.250  -0.3926   0.10707   0.10487  -0.0207   0.9972   0.0144
  -8.000  -0.3795   0.10341   0.10121  -0.0243   0.9955   0.0152
  -7.750  -0.3669   0.09984   0.09764  -0.0277   0.9932   0.0157
  -7.500  -0.3554   0.09643   0.09423  -0.0320   0.9896   0.0165
  -7.250  -0.3434   0.09313   0.09094  -0.0383   0.9858   0.0169
  -7.000  -0.3284   0.08939   0.08720  -0.0427   0.9819   0.0170
  -6.750  -0.3113   0.08507   0.08289  -0.0478   0.9772   0.0170
  -6.500  -0.2853   0.07994   0.07774  -0.0556   0.9743   0.0171
  -6.250  -0.2701   0.07439   0.07219  -0.0597   0.9729   0.0179
  -6.000  -0.2591   0.07192   0.06973  -0.0606   0.9681   0.0185
  -5.750  -0.2370   0.06835   0.06615  -0.0657   0.9643   0.0195
  -5.500  -0.2018   0.06338   0.06113  -0.0753   0.9620   0.0215
  -5.250  -0.1376   0.05627   0.05390  -0.0941   0.9604   0.0236
  -5.000  -0.0887   0.04933   0.04683  -0.1066   0.9596   0.0237
  -4.750  -0.0605   0.04019   0.03751  -0.1162   0.9540   0.0247
  -4.500  -0.0255   0.03682   0.03403  -0.1213   0.9522   0.0256
  -4.250   0.0171   0.03282   0.02982  -0.1278   0.9511   0.0272
  -4.000   0.1163   0.01845   0.01381  -0.1478   0.9596   0.0229
  -3.750   0.1575   0.01571   0.01050  -0.1513   0.9597   0.0247
  -3.500   0.1843   0.01498   0.00969  -0.1514   0.9564   0.0270
  -3.250   0.2142   0.01453   0.00915  -0.1518   0.9537   0.0298
  -3.000   0.2460   0.01443   0.00895  -0.1526   0.9516   0.0327
  -2.750   0.2822   0.01313   0.00752  -0.1546   0.9512   0.0372
  -2.500   0.3165   0.01287   0.00723  -0.1560   0.9498   0.0418
  -2.250   0.3517   0.01263   0.00694  -0.1575   0.9487   0.0445
  -2.000   0.3881   0.01193   0.00623  -0.1595   0.9480   0.0505
  -1.750   0.4238   0.01165   0.00594  -0.1612   0.9472   0.0548
  -1.500   0.4607   0.01131   0.00558  -0.1631   0.9465   0.0609
  -1.250   0.4837   0.01110   0.00538  -0.1620   0.9405   0.0699
  -1.000   0.5217   0.01057   0.00499  -0.1641   0.9381   0.1076
  -0.750   0.5606   0.01001   0.00479  -0.1666   0.9366   0.2283
  -0.500   0.5998   0.00939   0.00469  -0.1693   0.9355   0.4219
  -0.250   0.6394   0.00881   0.00457  -0.1719   0.9345   0.5986
   0.000   0.6786   0.00789   0.00431  -0.1739   0.9334   0.8373
   0.250   0.6979   0.00733   0.00390  -0.1712   0.9243   1.0000
   0.500   0.7441   0.00680   0.00333  -0.1747   0.9208   1.0000
   0.750   0.7723   0.00654   0.00305  -0.1743   0.9107   1.0000
   1.000   0.8050   0.00626   0.00274  -0.1749   0.8988   1.0000
   1.250   0.8410   0.00600   0.00244  -0.1763   0.8816   1.0000
   1.500   0.8758   0.00587   0.00226  -0.1774   0.8582   1.0000
   1.750   0.9116   0.00586   0.00208  -0.1788   0.8170   1.0000
   2.000   0.9373   0.00625   0.00208  -0.1779   0.7415   1.0000
   2.250   0.9455   0.00737   0.00241  -0.1734   0.5898   1.0000
   2.500   0.9612   0.00824   0.00282  -0.1710   0.5109   1.0000
   2.750   0.9817   0.00885   0.00313  -0.1695   0.4408   1.0000
   3.000   0.9954   0.01023   0.00368  -0.1671   0.2800   1.0000
   3.250   1.0156   0.01113   0.00412  -0.1658   0.1887   1.0000
   3.500   1.0328   0.01249   0.00480  -0.1640   0.0614   1.0000
   3.750   1.0569   0.01297   0.00521  -0.1632   0.0474   1.0000
   4.000   1.0815   0.01337   0.00562  -0.1626   0.0442   1.0000
   4.250   1.1058   0.01382   0.00609  -0.1618   0.0419   1.0000
   4.500   1.1293   0.01437   0.00671  -0.1609   0.0396   1.0000
   4.750   1.1526   0.01492   0.00733  -0.1599   0.0383   1.0000
   5.000   1.1759   0.01544   0.00791  -0.1590   0.0371   1.0000
   5.250   1.1987   0.01602   0.00855  -0.1580   0.0350   1.0000
   5.500   1.2207   0.01672   0.00930  -0.1569   0.0328   1.0000
   5.750   1.2412   0.01764   0.01026  -0.1555   0.0304   1.0000
   6.000   1.2582   0.01943   0.01218  -0.1535   0.0274   1.0000
   6.250   1.2822   0.01979   0.01260  -0.1528   0.0259   1.0000
   6.500   1.3046   0.02054   0.01342  -0.1517   0.0238   1.0000
   6.750   1.3267   0.02124   0.01416  -0.1507   0.0217   1.0000
   7.000   1.3465   0.02388   0.01683  -0.1496   0.0190   1.0000
   7.250   1.3691   0.02400   0.01708  -0.1485   0.0181   1.0000
   7.500   1.3915   0.02487   0.01807  -0.1475   0.0167   1.0000
   7.750   1.4132   0.02579   0.01908  -0.1464   0.0155   1.0000
   8.000   1.4338   0.02654   0.01990  -0.1452   0.0146   1.0000
   8.250   1.4534   0.02809   0.02151  -0.1441   0.0136   1.0000
   8.500   1.4733   0.03034   0.02403  -0.1427   0.0127   1.0000
   8.750   1.4926   0.03192   0.02585  -0.1412   0.0119   1.0000
   9.000   1.5099   0.03431   0.02852  -0.1394   0.0113   1.0000
   9.250   1.5249   0.03649   0.03095  -0.1374   0.0108   1.0000
   9.500   1.5374   0.03869   0.03341  -0.1350   0.0104   1.0000
   9.750   1.5479   0.04055   0.03547  -0.1325   0.0100   1.0000
  10.000   1.5558   0.04241   0.03752  -0.1298   0.0097   1.0000
  10.250   1.5557   0.04574   0.04117  -0.1260   0.0095   1.0000
  10.500   1.5437   0.04968   0.04545  -0.1205   0.0094   1.0000
  10.750   1.5279   0.05374   0.04984  -0.1149   0.0094   1.0000
  11.000   1.5074   0.05816   0.05457  -0.1096   0.0093   1.0000
  11.250   1.4849   0.06307   0.05979  -0.1050   0.0094   1.0000
  11.500   1.4625   0.06821   0.06522  -0.1015   0.0095   1.0000
  12.000   1.3091   0.10082   0.09893  -0.1046   0.0115   1.0000
  12.250   1.2837   0.11052   0.10878  -0.1110   0.0115   1.0000
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