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EPPLER 397 AIRFOIL (e397-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 397 AIRFOIL (e397-il)
Reynolds number: 200,000
Max Cl/Cd: 89.05 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e397-il-200000.txt
Download as CSV file: xf-e397-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2160   0.10500   0.10167  -0.0837   0.9728   0.0553
 -10.250  -0.3601   0.05808   0.05450  -0.1146   0.9600   0.0239
 -10.000  -0.3717   0.04952   0.04572  -0.1267   0.9488   0.0237
  -9.750  -0.3765   0.04233   0.03816  -0.1386   0.9368   0.0236
  -9.500  -0.3637   0.03626   0.03143  -0.1477   0.9307   0.0237
  -9.250  -0.3540   0.03275   0.02743  -0.1498   0.9219   0.0241
  -9.000  -0.3290   0.02968   0.02419  -0.1525   0.9178   0.0253
  -8.750  -0.2969   0.02746   0.02171  -0.1556   0.9152   0.0272
  -8.500  -0.2784   0.02602   0.01989  -0.1554   0.9071   0.0294
  -8.250  -0.2494   0.02441   0.01828  -0.1572   0.9031   0.0333
  -8.000  -0.2172   0.02259   0.01622  -0.1593   0.9002   0.0384
  -7.750  -0.1958   0.02198   0.01545  -0.1588   0.8931   0.0441
  -7.500  -0.1673   0.02092   0.01435  -0.1599   0.8885   0.0520
  -7.250  -0.1346   0.01994   0.01329  -0.1615   0.8853   0.0615
  -7.000  -0.1117   0.01928   0.01256  -0.1612   0.8792   0.0703
  -6.750  -0.0843   0.01860   0.01177  -0.1616   0.8743   0.0805
  -6.500  -0.0526   0.01797   0.01102  -0.1627   0.8709   0.0922
  -6.250  -0.0247   0.01759   0.01055  -0.1631   0.8663   0.1043
  -6.000  -0.0002   0.01715   0.01010  -0.1629   0.8605   0.1174
  -5.750   0.0302   0.01669   0.00958  -0.1636   0.8568   0.1330
  -5.500   0.0623   0.01616   0.00907  -0.1648   0.8540   0.1506
  -5.250   0.0842   0.01601   0.00894  -0.1640   0.8477   0.1666
  -5.000   0.1128   0.01575   0.00867  -0.1644   0.8433   0.1857
  -4.750   0.1442   0.01551   0.00836  -0.1652   0.8402   0.2069
  -4.500   0.1717   0.01536   0.00823  -0.1654   0.8361   0.2267
  -4.250   0.1966   0.01530   0.00818  -0.1651   0.8308   0.2458
  -4.000   0.2263   0.01516   0.00801  -0.1656   0.8270   0.2672
  -3.750   0.2578   0.01501   0.00783  -0.1663   0.8242   0.2887
  -3.500   0.2824   0.01504   0.00790  -0.1660   0.8194   0.3076
  -3.250   0.3089   0.01503   0.00789  -0.1659   0.8147   0.3275
  -3.000   0.3391   0.01496   0.00776  -0.1663   0.8112   0.3488
  -2.750   0.3703   0.01484   0.00766  -0.1670   0.8086   0.3691
  -2.500   0.3934   0.01495   0.00783  -0.1664   0.8034   0.3877
  -2.250   0.4204   0.01497   0.00786  -0.1663   0.7990   0.4079
  -2.000   0.4505   0.01491   0.00779  -0.1668   0.7957   0.4296
  -1.750   0.4818   0.01483   0.00774  -0.1674   0.7931   0.4509
  -1.500   0.5039   0.01501   0.00799  -0.1665   0.7877   0.4714
  -1.250   0.5308   0.01505   0.00806  -0.1665   0.7835   0.4937
  -1.000   0.5607   0.01499   0.00806  -0.1668   0.7803   0.5171
  -0.750   0.5922   0.01494   0.00802  -0.1674   0.7778   0.5425
  -0.500   0.6129   0.01517   0.00837  -0.1663   0.7721   0.5658
  -0.250   0.6395   0.01521   0.00850  -0.1661   0.7680   0.5920
   0.000   0.6694   0.01517   0.00850  -0.1664   0.7648   0.6208
   0.250   0.7004   0.01512   0.00850  -0.1669   0.7623   0.6514
   0.500   0.7187   0.01541   0.00895  -0.1653   0.7563   0.6799
   0.750   0.7446   0.01543   0.00907  -0.1648   0.7521   0.7124
   1.000   0.7728   0.01536   0.00908  -0.1646   0.7491   0.7465
   1.250   0.7967   0.01541   0.00924  -0.1636   0.7454   0.7823
   1.500   0.8128   0.01560   0.00958  -0.1612   0.7395   0.8221
   1.750   0.8326   0.01549   0.00957  -0.1591   0.7356   0.8700
   2.000   0.8582   0.01519   0.00934  -0.1580   0.7327   0.9595
   2.250   0.8849   0.01553   0.00968  -0.1584   0.7269   1.0000
   2.500   0.9143   0.01567   0.00978  -0.1590   0.7220   1.0000
   2.750   0.9485   0.01564   0.00969  -0.1603   0.7186   1.0000
   3.000   0.9755   0.01586   0.00991  -0.1603   0.7136   1.0000
   3.250   1.0006   0.01607   0.01013  -0.1600   0.7076   1.0000
   3.500   1.0339   0.01600   0.01004  -0.1609   0.7037   1.0000
   3.750   1.0604   0.01617   0.01021  -0.1608   0.6982   1.0000
   4.000   1.0860   0.01629   0.01036  -0.1605   0.6918   1.0000
   4.250   1.1202   0.01615   0.01019  -0.1615   0.6876   1.0000
   4.500   1.1418   0.01640   0.01052  -0.1604   0.6804   1.0000
   4.750   1.1719   0.01632   0.01044  -0.1607   0.6745   1.0000
   5.000   1.2002   0.01632   0.01047  -0.1607   0.6682   1.0000
   5.250   1.2258   0.01628   0.01047  -0.1602   0.6601   1.0000
   5.500   1.2529   0.01616   0.01037  -0.1598   0.6517   1.0000
   5.750   1.2826   0.01584   0.01003  -0.1597   0.6421   1.0000
   6.000   1.3031   0.01577   0.01003  -0.1581   0.6302   1.0000
   6.250   1.3258   0.01570   0.00999  -0.1570   0.6190   1.0000
   6.500   1.3509   0.01563   0.00994  -0.1562   0.6085   1.0000
   6.750   1.3728   0.01569   0.01007  -0.1550   0.5979   1.0000
   7.000   1.3923   0.01584   0.01031  -0.1535   0.5867   1.0000
   7.250   1.4130   0.01596   0.01049  -0.1521   0.5749   1.0000
   7.500   1.4328   0.01609   0.01069  -0.1505   0.5619   1.0000
   7.750   1.4495   0.01628   0.01091  -0.1484   0.5462   1.0000
   8.000   1.4635   0.01652   0.01118  -0.1458   0.5280   1.0000
   8.250   1.4746   0.01682   0.01146  -0.1426   0.5082   1.0000
   8.500   1.4815   0.01727   0.01189  -0.1388   0.4856   1.0000
   8.750   1.4873   0.01786   0.01241  -0.1350   0.4610   1.0000
   9.000   1.4912   0.01862   0.01311  -0.1311   0.4349   1.0000
   9.250   1.4924   0.01957   0.01397  -0.1269   0.4070   1.0000
   9.500   1.4895   0.02082   0.01507  -0.1225   0.3762   1.0000
   9.750   1.4846   0.02232   0.01643  -0.1182   0.3451   1.0000
  10.000   1.4792   0.02403   0.01800  -0.1141   0.3150   1.0000
  10.250   1.4737   0.02594   0.01976  -0.1104   0.2855   1.0000
  10.500   1.4689   0.02797   0.02167  -0.1071   0.2577   1.0000
  10.750   1.4647   0.03013   0.02371  -0.1042   0.2313   1.0000
  11.000   1.4602   0.03244   0.02592  -0.1015   0.2063   1.0000
  11.250   1.4568   0.03482   0.02820  -0.0991   0.1805   1.0000
  11.500   1.4526   0.03740   0.03066  -0.0969   0.1550   1.0000
  11.750   1.4474   0.04018   0.03332  -0.0948   0.1304   1.0000
  12.000   1.4418   0.04316   0.03616  -0.0929   0.1096   1.0000
  12.250   1.4381   0.04608   0.03900  -0.0913   0.0940   1.0000
  12.500   1.4357   0.04899   0.04186  -0.0899   0.0823   1.0000
  12.750   1.4371   0.05161   0.04449  -0.0888   0.0722   1.0000
  13.000   1.4384   0.05430   0.04721  -0.0879   0.0639   1.0000
  13.250   1.4361   0.05748   0.05039  -0.0869   0.0574   1.0000
  13.500   1.4326   0.06089   0.05382  -0.0861   0.0518   1.0000
  13.750   1.4293   0.06438   0.05739  -0.0853   0.0468   1.0000
  14.000   1.4258   0.06796   0.06101  -0.0847   0.0425   1.0000
  14.250   1.4230   0.07155   0.06468  -0.0841   0.0383   1.0000
  14.500   1.4240   0.07478   0.06800  -0.0839   0.0345   1.0000
  14.750   1.4219   0.07835   0.07157  -0.0834   0.0315   1.0000
  15.000   1.4250   0.08146   0.07485  -0.0835   0.0285   1.0000
  15.250   1.4254   0.08488   0.07829  -0.0837   0.0263   1.0000
  15.500   1.4269   0.08823   0.08176  -0.0837   0.0241   1.0000
  15.750   1.4289   0.09158   0.08522  -0.0840   0.0223   1.0000
  16.000   1.4305   0.09492   0.08861  -0.0844   0.0210   1.0000
  16.250   1.4339   0.09794   0.09169  -0.0842   0.0197   1.0000
  16.500   1.4370   0.10121   0.09514  -0.0844   0.0186   1.0000
  16.750   1.4385   0.10471   0.09877  -0.0851   0.0176   1.0000
  17.000   1.4398   0.10819   0.10230  -0.0859   0.0168   1.0000
  17.250   1.4429   0.11126   0.10540  -0.0861   0.0158   1.0000
  17.500   1.4405   0.11559   0.10999  -0.0874   0.0152   1.0000
  17.750   1.4386   0.11983   0.11443  -0.0888   0.0146   1.0000
  18.000   1.4375   0.12393   0.11871  -0.0901   0.0142   1.0000
  18.250   1.4352   0.12826   0.12322  -0.0917   0.0139   1.0000
  18.500   1.4318   0.13286   0.12799  -0.0937   0.0135   1.0000
  18.750   1.4280   0.13754   0.13283  -0.0958   0.0133   1.0000
  19.000   1.4238   0.14232   0.13777  -0.0982   0.0131   1.0000
  19.250   1.4188   0.14730   0.14289  -0.1008   0.0129   1.0000
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