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EPPLER 397 AIRFOIL (e397-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 397 AIRFOIL (e397-il)
Reynolds number: 500,000
Max Cl/Cd: 135.71 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e397-il-500000.txt
Download as CSV file: xf-e397-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 397 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
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.4873   0.07429   0.07157  -0.0867   0.9931   0.0074
 -12.500  -0.5004   0.06540   0.06254  -0.0953   0.9886   0.0075
 -12.250  -0.5077   0.05692   0.05388  -0.1051   0.9841   0.0075
 -12.000  -0.5150   0.04915   0.04590  -0.1141   0.9755   0.0074
 -11.750  -0.5124   0.04275   0.03931  -0.1227   0.9665   0.0073
 -11.500  -0.5039   0.03668   0.03306  -0.1321   0.9578   0.0074
 -11.000  -0.4624   0.02689   0.02281  -0.1526   0.9344   0.0078
 -10.750  -0.4377   0.02445   0.02012  -0.1577   0.9228   0.0082
 -10.500  -0.4162   0.02271   0.01815  -0.1601   0.9113   0.0086
 -10.250  -0.3971   0.02125   0.01647  -0.1611   0.9001   0.0089
 -10.000  -0.3778   0.02027   0.01529  -0.1611   0.8896   0.0093
  -9.750  -0.3613   0.01868   0.01354  -0.1614   0.8802   0.0098
  -9.500  -0.3400   0.01775   0.01249  -0.1615   0.8719   0.0104
  -9.250  -0.3172   0.01698   0.01158  -0.1616   0.8643   0.0112
  -9.000  -0.2934   0.01628   0.01071  -0.1616   0.8571   0.0121
  -8.750  -0.2704   0.01530   0.00963  -0.1618   0.8507   0.0137
  -8.500  -0.2457   0.01465   0.00887  -0.1619   0.8442   0.0158
  -8.250  -0.2193   0.01414   0.00827  -0.1622   0.8388   0.0191
  -8.000  -0.1941   0.01356   0.00764  -0.1622   0.8327   0.0238
  -7.750  -0.1676   0.01310   0.00712  -0.1624   0.8272   0.0295
  -7.500  -0.1402   0.01268   0.00665  -0.1628   0.8226   0.0360
  -7.250  -0.1139   0.01226   0.00622  -0.1629   0.8172   0.0428
  -7.000  -0.0866   0.01188   0.00580  -0.1631   0.8123   0.0500
  -6.500  -0.0312   0.01133   0.00517  -0.1636   0.8031   0.0672
  -6.250  -0.0034   0.01108   0.00490  -0.1638   0.7986   0.0770
  -6.000   0.0249   0.01080   0.00459  -0.1642   0.7945   0.0889
  -5.750   0.0530   0.01056   0.00434  -0.1645   0.7904   0.1015
  -5.500   0.0809   0.01033   0.00413  -0.1647   0.7859   0.1155
  -5.250   0.1092   0.01013   0.00392  -0.1649   0.7819   0.1307
  -5.000   0.1382   0.00998   0.00374  -0.1653   0.7783   0.1466
  -4.750   0.1664   0.00983   0.00360  -0.1655   0.7743   0.1626
  -4.500   0.1946   0.00967   0.00347  -0.1658   0.7702   0.1799
  -4.250   0.2232   0.00953   0.00334  -0.1661   0.7665   0.1979
  -4.000   0.2524   0.00944   0.00324  -0.1665   0.7631   0.2161
  -3.750   0.2807   0.00935   0.00317  -0.1667   0.7594   0.2340
  -3.500   0.3091   0.00926   0.00310  -0.1669   0.7555   0.2514
  -3.250   0.3378   0.00919   0.00303  -0.1672   0.7519   0.2691
  -3.000   0.3669   0.00915   0.00297  -0.1675   0.7487   0.2868
  -2.750   0.3956   0.00911   0.00294  -0.1678   0.7453   0.3038
  -2.500   0.4238   0.00905   0.00292  -0.1679   0.7415   0.3210
  -2.250   0.4524   0.00900   0.00289  -0.1682   0.7379   0.3382
  -2.000   0.4813   0.00897   0.00286  -0.1684   0.7346   0.3558
  -1.750   0.5107   0.00898   0.00287  -0.1688   0.7315   0.3733
  -1.500   0.5385   0.00894   0.00288  -0.1689   0.7279   0.3915
  -1.250   0.5669   0.00891   0.00289  -0.1691   0.7242   0.4101
  -1.000   0.5956   0.00889   0.00289  -0.1693   0.7208   0.4294
  -0.750   0.6248   0.00889   0.00291  -0.1697   0.7177   0.4495
  -0.500   0.6531   0.00889   0.00297  -0.1699   0.7143   0.4704
   0.000   0.7095   0.00885   0.00305  -0.1701   0.7070   0.5149
   0.250   0.7383   0.00886   0.00309  -0.1704   0.7037   0.5391
   0.500   0.7670   0.00889   0.00317  -0.1706   0.7004   0.5638
   0.750   0.7943   0.00888   0.00326  -0.1706   0.6964   0.5895
   1.000   0.8223   0.00887   0.00333  -0.1707   0.6925   0.6167
   1.250   0.8505   0.00887   0.00338  -0.1708   0.6889   0.6443
   1.500   0.8788   0.00891   0.00349  -0.1709   0.6852   0.6731
   1.750   0.9053   0.00889   0.00359  -0.1707   0.6808   0.7024
   2.000   0.9324   0.00888   0.00367  -0.1705   0.6764   0.7331
   2.250   0.9598   0.00889   0.00374  -0.1704   0.6725   0.7653
   2.500   0.9852   0.00889   0.00386  -0.1699   0.6679   0.7994
   2.750   1.0095   0.00885   0.00395  -0.1691   0.6627   0.8372
   3.000   1.0321   0.00881   0.00398  -0.1678   0.6580   0.8811
   3.250   1.0523   0.00868   0.00399  -0.1659   0.6531   0.9743
   3.500   1.0801   0.00873   0.00405  -0.1660   0.6475   1.0000
   3.750   1.1083   0.00882   0.00408  -0.1662   0.6415   1.0000
   4.000   1.1329   0.00884   0.00415  -0.1656   0.6320   1.0000
   4.250   1.1584   0.00890   0.00418  -0.1651   0.6223   1.0000
   4.500   1.1834   0.00898   0.00423  -0.1646   0.6125   1.0000
   4.750   1.2086   0.00907   0.00436  -0.1642   0.6033   1.0000
   5.000   1.2339   0.00920   0.00446  -0.1637   0.5951   1.0000
   5.250   1.2585   0.00931   0.00460  -0.1632   0.5849   1.0000
   5.500   1.2830   0.00946   0.00476  -0.1626   0.5753   1.0000
   5.750   1.3067   0.00963   0.00492  -0.1619   0.5653   1.0000
   6.000   1.3300   0.00980   0.00511  -0.1611   0.5536   1.0000
   6.250   1.3525   0.01000   0.00531  -0.1601   0.5408   1.0000
   6.500   1.3736   0.01024   0.00554  -0.1589   0.5260   1.0000
   6.750   1.3924   0.01054   0.00580  -0.1573   0.5082   1.0000
   7.000   1.4094   0.01090   0.00611  -0.1553   0.4874   1.0000
   7.250   1.4222   0.01133   0.00646  -0.1526   0.4632   1.0000
   7.500   1.4305   0.01188   0.00691  -0.1490   0.4348   1.0000
   7.750   1.4371   0.01255   0.00745  -0.1453   0.4052   1.0000
   8.000   1.4420   0.01335   0.00810  -0.1414   0.3740   1.0000
   8.250   1.4444   0.01430   0.00889  -0.1372   0.3413   1.0000
   8.500   1.4463   0.01536   0.00979  -0.1332   0.3088   1.0000
   8.750   1.4485   0.01650   0.01078  -0.1295   0.2783   1.0000
   9.000   1.4504   0.01775   0.01189  -0.1260   0.2489   1.0000
   9.250   1.4521   0.01910   0.01310  -0.1226   0.2203   1.0000
   9.500   1.4555   0.02045   0.01434  -0.1197   0.1951   1.0000
   9.750   1.4588   0.02189   0.01567  -0.1169   0.1715   1.0000
  10.000   1.4611   0.02348   0.01713  -0.1142   0.1487   1.0000
  10.250   1.4634   0.02515   0.01869  -0.1116   0.1247   1.0000
  10.500   1.4656   0.02691   0.02034  -0.1092   0.1038   1.0000
  10.750   1.4675   0.02876   0.02210  -0.1069   0.0849   1.0000
  11.000   1.4708   0.03059   0.02385  -0.1049   0.0678   1.0000
  11.250   1.4746   0.03243   0.02562  -0.1030   0.0572   1.0000
  11.500   1.4793   0.03426   0.02744  -0.1014   0.0513   1.0000
  11.750   1.4869   0.03590   0.02914  -0.1000   0.0477   1.0000
  12.000   1.4925   0.03774   0.03102  -0.0986   0.0442   1.0000
  12.250   1.4952   0.03993   0.03325  -0.0971   0.0403   1.0000
  12.500   1.5068   0.04132   0.03474  -0.0962   0.0372   1.0000
  12.750   1.5118   0.04338   0.03682  -0.0951   0.0333   1.0000
  13.000   1.5206   0.04511   0.03862  -0.0942   0.0291   1.0000
  13.250   1.5260   0.04721   0.04071  -0.0932   0.0247   1.0000
  13.500   1.5304   0.04949   0.04297  -0.0923   0.0204   1.0000
  13.750   1.5343   0.05188   0.04541  -0.0914   0.0174   1.0000
  14.000   1.5351   0.05470   0.04828  -0.0906   0.0150   1.0000
  14.250   1.5363   0.05753   0.05116  -0.0899   0.0132   1.0000
  14.500   1.5357   0.06067   0.05440  -0.0892   0.0118   1.0000
  14.750   1.5377   0.06357   0.05740  -0.0888   0.0108   1.0000
  15.000   1.5356   0.06706   0.06096  -0.0885   0.0100   1.0000
  15.250   1.5319   0.07087   0.06489  -0.0882   0.0093   1.0000
  15.500   1.5337   0.07402   0.06815  -0.0882   0.0086   1.0000
  15.750   1.5341   0.07743   0.07165  -0.0883   0.0080   1.0000
  16.000   1.5321   0.08125   0.07555  -0.0886   0.0076   1.0000
  16.250   1.5220   0.08636   0.08077  -0.0891   0.0072   1.0000
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