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EPPLER 396 AIRFOIL (e396-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 396 AIRFOIL (e396-il)
Reynolds number: 200,000
Max Cl/Cd: 89.3 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e396-il-200000.txt
Download as CSV file: xf-e396-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 396 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.1904   0.08819   0.08488  -0.0911   0.9624   0.0383
  -9.250  -0.1782   0.08221   0.07887  -0.0960   0.9592   0.0337
  -9.000  -0.2545   0.05343   0.05007  -0.1210   0.9450   0.0261
  -8.750  -0.2685   0.03872   0.03468  -0.1459   0.9306   0.0251
  -8.500  -0.2638   0.03372   0.02911  -0.1500   0.9199   0.0254
  -8.250  -0.2356   0.02930   0.02403  -0.1552   0.9167   0.0264
  -8.000  -0.2185   0.02717   0.02147  -0.1553   0.9082   0.0276
  -7.750  -0.1886   0.02456   0.01864  -0.1579   0.9046   0.0310
  -7.500  -0.1524   0.02335   0.01715  -0.1604   0.9021   0.0359
  -7.250  -0.1343   0.02165   0.01531  -0.1597   0.8943   0.0402
  -7.000  -0.1013   0.02062   0.01403  -0.1613   0.8905   0.0485
  -6.750  -0.0661   0.01985   0.01314  -0.1632   0.8877   0.0582
  -6.500  -0.0455   0.01911   0.01241  -0.1625   0.8804   0.0662
  -6.250  -0.0144   0.01828   0.01146  -0.1635   0.8763   0.0764
  -6.000   0.0195   0.01755   0.01061  -0.1649   0.8733   0.0880
  -5.750   0.0422   0.01734   0.01028  -0.1642   0.8665   0.0985
  -5.500   0.0723   0.01679   0.00969  -0.1649   0.8622   0.1125
  -5.250   0.1051   0.01618   0.00906  -0.1660   0.8590   0.1287
  -5.000   0.1284   0.01595   0.00886  -0.1655   0.8526   0.1442
  -4.750   0.1578   0.01562   0.00852  -0.1660   0.8481   0.1621
  -4.500   0.1902   0.01532   0.00815  -0.1669   0.8448   0.1833
  -4.250   0.2146   0.01520   0.00805  -0.1665   0.8389   0.2022
  -4.000   0.2432   0.01502   0.00789  -0.1668   0.8342   0.2234
  -3.750   0.2748   0.01480   0.00762  -0.1676   0.8308   0.2463
  -3.500   0.3005   0.01475   0.00761  -0.1673   0.8254   0.2673
  -3.250   0.3281   0.01467   0.00752  -0.1674   0.8204   0.2899
  -3.000   0.3591   0.01451   0.00737  -0.1680   0.8168   0.3131
  -2.750   0.3864   0.01448   0.00734  -0.1680   0.8122   0.3358
  -2.500   0.4125   0.01446   0.00736  -0.1678   0.8068   0.3582
  -2.250   0.4429   0.01434   0.00725  -0.1682   0.8030   0.3826
  -2.000   0.4723   0.01429   0.00720  -0.1685   0.7992   0.4082
  -1.750   0.4965   0.01433   0.00733  -0.1680   0.7932   0.4314
  -1.500   0.5262   0.01425   0.00727  -0.1683   0.7891   0.4582
  -1.250   0.5578   0.01415   0.00719  -0.1689   0.7861   0.4875
  -1.000   0.5800   0.01427   0.00742  -0.1680   0.7796   0.5150
  -0.750   0.6088   0.01421   0.00742  -0.1682   0.7752   0.5459
  -0.500   0.6397   0.01411   0.00737  -0.1686   0.7720   0.5792
  -0.250   0.6620   0.01423   0.00763  -0.1676   0.7657   0.6116
   0.000   0.6896   0.01420   0.00768  -0.1674   0.7611   0.6488
   0.250   0.7192   0.01409   0.00765  -0.1675   0.7577   0.6877
   0.500   0.7398   0.01422   0.00793  -0.1661   0.7515   0.7268
   0.750   0.7641   0.01417   0.00799  -0.1651   0.7467   0.7706
   1.000   0.7892   0.01404   0.00793  -0.1640   0.7432   0.8192
   1.250   0.8016   0.01410   0.00816  -0.1606   0.7368   0.8780
   1.500   0.8290   0.01390   0.00800  -0.1601   0.7320   1.0000
   1.750   0.8640   0.01393   0.00790  -0.1616   0.7285   1.0000
   2.000   0.8878   0.01422   0.00821  -0.1613   0.7217   1.0000
   2.250   0.9186   0.01428   0.00821  -0.1619   0.7169   1.0000
   2.500   0.9507   0.01435   0.00820  -0.1627   0.7129   1.0000
   2.750   0.9739   0.01461   0.00850  -0.1621   0.7058   1.0000
   3.000   1.0052   0.01463   0.00847  -0.1627   0.7012   1.0000
   3.250   1.0312   0.01483   0.00867  -0.1625   0.6951   1.0000
   3.500   1.0588   0.01493   0.00877  -0.1625   0.6890   1.0000
   3.750   1.0920   0.01491   0.00870  -0.1634   0.6848   1.0000
   4.000   1.1131   0.01517   0.00904  -0.1623   0.6767   1.0000
   4.250   1.1446   0.01514   0.00896  -0.1629   0.6714   1.0000
   4.500   1.1675   0.01533   0.00923  -0.1620   0.6633   1.0000
   4.750   1.1980   0.01528   0.00916  -0.1624   0.6572   1.0000
   5.000   1.2210   0.01546   0.00940  -0.1615   0.6489   1.0000
   5.250   1.2513   0.01541   0.00933  -0.1618   0.6424   1.0000
   5.500   1.2730   0.01557   0.00958  -0.1607   0.6332   1.0000
   5.750   1.3022   0.01554   0.00954  -0.1608   0.6257   1.0000
   6.000   1.3245   0.01565   0.00973  -0.1597   0.6161   1.0000
   6.250   1.3481   0.01576   0.00989  -0.1589   0.6068   1.0000
   6.500   1.3753   0.01575   0.00989  -0.1586   0.5975   1.0000
   6.750   1.3960   0.01587   0.01007  -0.1572   0.5860   1.0000
   7.000   1.4166   0.01601   0.01029  -0.1558   0.5741   1.0000
   7.250   1.4374   0.01616   0.01048  -0.1544   0.5618   1.0000
   7.500   1.4574   0.01632   0.01069  -0.1529   0.5486   1.0000
   7.750   1.4754   0.01653   0.01095  -0.1510   0.5336   1.0000
   8.000   1.4919   0.01678   0.01122  -0.1489   0.5173   1.0000
   8.250   1.5067   0.01709   0.01153  -0.1465   0.4997   1.0000
   8.500   1.5186   0.01748   0.01192  -0.1436   0.4812   1.0000
   8.750   1.5252   0.01795   0.01240  -0.1398   0.4610   1.0000
   9.000   1.5311   0.01855   0.01294  -0.1360   0.4396   1.0000
   9.250   1.5343   0.01930   0.01366  -0.1320   0.4154   1.0000
   9.500   1.5356   0.02023   0.01455  -0.1279   0.3898   1.0000
   9.750   1.5344   0.02139   0.01562  -0.1238   0.3624   1.0000
  10.000   1.5315   0.02279   0.01690  -0.1197   0.3343   1.0000
  10.250   1.5273   0.02443   0.01842  -0.1158   0.3063   1.0000
  10.500   1.5225   0.02629   0.02016  -0.1122   0.2791   1.0000
  10.750   1.5177   0.02832   0.02209  -0.1089   0.2530   1.0000
  11.000   1.5133   0.03050   0.02417  -0.1059   0.2273   1.0000
  11.250   1.5090   0.03282   0.02639  -0.1033   0.2032   1.0000
  11.500   1.5039   0.03534   0.02881  -0.1008   0.1809   1.0000
  11.750   1.5001   0.03789   0.03129  -0.0987   0.1585   1.0000
  12.000   1.4954   0.04066   0.03397  -0.0968   0.1384   1.0000
  12.250   1.4917   0.04348   0.03672  -0.0951   0.1192   1.0000
  12.500   1.4864   0.04658   0.03974  -0.0935   0.1027   1.0000
  13.000   1.4759   0.05318   0.04626  -0.0909   0.0763   1.0000
  13.250   1.4725   0.05648   0.04956  -0.0900   0.0657   1.0000
  13.500   1.4699   0.05980   0.05293  -0.0891   0.0569   1.0000
  13.750   1.4646   0.06353   0.05668  -0.0884   0.0504   1.0000
  14.000   1.4615   0.06711   0.06030  -0.0880   0.0448   1.0000
  14.250   1.4570   0.07096   0.06423  -0.0876   0.0401   1.0000
  14.500   1.4562   0.07445   0.06780  -0.0875   0.0358   1.0000
  14.750   1.4478   0.07893   0.07227  -0.0872   0.0326   1.0000
  15.000   1.4499   0.08221   0.07572  -0.0873   0.0294   1.0000
  15.250   1.4486   0.08598   0.07957  -0.0876   0.0268   1.0000
  15.500   1.4428   0.09023   0.08381  -0.0875   0.0244   1.0000
  15.750   1.4446   0.09367   0.08744  -0.0878   0.0227   1.0000
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