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EPPLER 396 AIRFOIL (e396-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 396 AIRFOIL (e396-il)
Reynolds number: 200,000
Max Cl/Cd: 90.29 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e396-il-200000-n5.txt
Download as CSV file: xf-e396-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3649   0.06134   0.05753  -0.1026   0.9488   0.0111
 -10.500  -0.3803   0.05080   0.04677  -0.1147   0.9374   0.0110
 -10.250  -0.3826   0.04202   0.03770  -0.1272   0.9252   0.0110
 -10.000  -0.3764   0.03446   0.02973  -0.1408   0.9110   0.0111
  -9.750  -0.3579   0.03061   0.02546  -0.1473   0.9020   0.0113
  -9.500  -0.3429   0.02794   0.02256  -0.1501   0.8919   0.0117
  -9.250  -0.3205   0.02601   0.02041  -0.1524   0.8847   0.0123
  -9.000  -0.2984   0.02447   0.01866  -0.1537   0.8769   0.0129
  -8.750  -0.2741   0.02300   0.01695  -0.1550   0.8705   0.0140
  -8.500  -0.2507   0.02181   0.01548  -0.1555   0.8634   0.0154
  -8.250  -0.2241   0.02068   0.01422  -0.1568   0.8581   0.0175
  -8.000  -0.2002   0.01987   0.01326  -0.1570   0.8510   0.0201
  -7.750  -0.1736   0.01882   0.01205  -0.1578   0.8456   0.0230
  -7.500  -0.1475   0.01814   0.01122  -0.1581   0.8399   0.0269
  -7.250  -0.1212   0.01745   0.01045  -0.1585   0.8341   0.0319
  -7.000  -0.0925   0.01689   0.00972  -0.1591   0.8297   0.0380
  -6.750  -0.0667   0.01641   0.00917  -0.1593   0.8238   0.0445
  -6.500  -0.0392   0.01590   0.00858  -0.1596   0.8188   0.0514
  -6.250  -0.0102   0.01552   0.00803  -0.1601   0.8146   0.0590
  -6.000   0.0161   0.01509   0.00760  -0.1602   0.8090   0.0676
  -5.750   0.0440   0.01472   0.00716  -0.1605   0.8043   0.0772
  -5.500   0.0733   0.01440   0.00673  -0.1610   0.8004   0.0878
  -5.250   0.1000   0.01415   0.00644  -0.1610   0.7950   0.0994
  -5.000   0.1280   0.01388   0.00613  -0.1613   0.7904   0.1125
  -4.750   0.1572   0.01364   0.00583  -0.1617   0.7866   0.1265
  -4.500   0.1845   0.01345   0.00561  -0.1618   0.7816   0.1417
  -4.250   0.2124   0.01325   0.00542  -0.1620   0.7770   0.1579
  -4.000   0.2413   0.01308   0.00521  -0.1624   0.7731   0.1753
  -3.750   0.2694   0.01294   0.00506  -0.1625   0.7687   0.1927
  -3.500   0.2970   0.01283   0.00494  -0.1626   0.7639   0.2109
  -3.250   0.3256   0.01272   0.00480  -0.1629   0.7599   0.2295
  -3.000   0.3546   0.01262   0.00468  -0.1632   0.7561   0.2484
  -2.750   0.3817   0.01255   0.00463  -0.1632   0.7512   0.2669
  -2.500   0.4099   0.01248   0.00455  -0.1633   0.7469   0.2863
  -2.250   0.4390   0.01242   0.00447  -0.1636   0.7433   0.3060
  -2.000   0.4664   0.01237   0.00445  -0.1636   0.7387   0.3256
  -1.750   0.4941   0.01234   0.00444  -0.1637   0.7341   0.3462
  -1.500   0.5226   0.01229   0.00440  -0.1639   0.7302   0.3669
  -1.250   0.5509   0.01227   0.00439  -0.1640   0.7263   0.3893
  -1.000   0.5779   0.01225   0.00443  -0.1639   0.7213   0.4114
  -0.750   0.6060   0.01223   0.00445  -0.1640   0.7171   0.4350
  -0.500   0.6350   0.01221   0.00444  -0.1643   0.7135   0.4601
  -0.250   0.6612   0.01222   0.00454  -0.1640   0.7083   0.4853
   0.000   0.6886   0.01222   0.00460  -0.1640   0.7037   0.5124
   0.250   0.7171   0.01221   0.00462  -0.1641   0.6999   0.5410
   0.500   0.7434   0.01222   0.00474  -0.1639   0.6949   0.5703
   0.750   0.7700   0.01223   0.00484  -0.1636   0.6900   0.6015
   1.000   0.7974   0.01223   0.00491  -0.1635   0.6859   0.6344
   1.250   0.8229   0.01225   0.00504  -0.1630   0.6809   0.6685
   1.500   0.8481   0.01227   0.00517  -0.1624   0.6757   0.7047
   1.750   0.8739   0.01226   0.00524  -0.1619   0.6715   0.7432
   2.000   0.8969   0.01227   0.00538  -0.1608   0.6662   0.7852
   2.250   0.9182   0.01226   0.00548  -0.1592   0.6609   0.8340
   2.500   0.9389   0.01216   0.00546  -0.1574   0.6564   0.9042
   2.750   0.9661   0.01219   0.00556  -0.1573   0.6505   1.0000
   3.000   0.9935   0.01232   0.00567  -0.1574   0.6448   1.0000
   3.250   1.0212   0.01246   0.00577  -0.1575   0.6395   1.0000
   3.500   1.0470   0.01261   0.00595  -0.1572   0.6327   1.0000
   3.750   1.0749   0.01273   0.00604  -0.1573   0.6272   1.0000
   4.000   1.0997   0.01290   0.00626  -0.1568   0.6197   1.0000
   4.250   1.1266   0.01303   0.00637  -0.1567   0.6133   1.0000
   4.500   1.1510   0.01321   0.00660  -0.1561   0.6049   1.0000
   4.750   1.1769   0.01335   0.00673  -0.1558   0.5973   1.0000
   5.000   1.2008   0.01353   0.00695  -0.1552   0.5880   1.0000
   5.250   1.2252   0.01371   0.00715  -0.1546   0.5793   1.0000
   5.500   1.2494   0.01390   0.00735  -0.1539   0.5700   1.0000
   5.750   1.2718   0.01411   0.00760  -0.1530   0.5591   1.0000
   6.000   1.2943   0.01434   0.00786  -0.1521   0.5482   1.0000
   6.250   1.3164   0.01458   0.00811  -0.1511   0.5371   1.0000
   6.500   1.3374   0.01485   0.00841  -0.1499   0.5247   1.0000
   6.750   1.3571   0.01515   0.00871  -0.1485   0.5108   1.0000
   7.000   1.3754   0.01549   0.00905  -0.1468   0.4957   1.0000
   7.250   1.3924   0.01586   0.00943  -0.1449   0.4796   1.0000
   7.500   1.4071   0.01627   0.00984  -0.1426   0.4629   1.0000
   7.750   1.4193   0.01675   0.01029  -0.1399   0.4445   1.0000
   8.000   1.4290   0.01734   0.01085  -0.1369   0.4239   1.0000
   8.250   1.4375   0.01801   0.01148  -0.1338   0.4011   1.0000
   8.500   1.4435   0.01884   0.01222  -0.1304   0.3771   1.0000
   8.750   1.4474   0.01982   0.01311  -0.1269   0.3523   1.0000
   9.000   1.4498   0.02095   0.01415  -0.1234   0.3255   1.0000
   9.250   1.4513   0.02225   0.01535  -0.1200   0.2993   1.0000
   9.500   1.4521   0.02370   0.01671  -0.1167   0.2739   1.0000
   9.750   1.4523   0.02531   0.01822  -0.1137   0.2497   1.0000
  10.000   1.4525   0.02704   0.01986  -0.1109   0.2258   1.0000
  10.250   1.4533   0.02884   0.02161  -0.1083   0.2032   1.0000
  10.500   1.4535   0.03079   0.02348  -0.1059   0.1822   1.0000
  10.750   1.4555   0.03270   0.02534  -0.1039   0.1626   1.0000
  11.000   1.4570   0.03473   0.02731  -0.1019   0.1445   1.0000
  11.250   1.4583   0.03686   0.02939  -0.1001   0.1281   1.0000
  11.500   1.4602   0.03901   0.03151  -0.0985   0.1127   1.0000
  11.750   1.4623   0.04123   0.03371  -0.0970   0.0987   1.0000
  12.000   1.4640   0.04355   0.03601  -0.0956   0.0859   1.0000
  12.250   1.4656   0.04596   0.03841  -0.0944   0.0745   1.0000
  12.500   1.4668   0.04849   0.04093  -0.0932   0.0642   1.0000
  12.750   1.4695   0.05094   0.04345  -0.0922   0.0555   1.0000
  13.000   1.4715   0.05353   0.04607  -0.0914   0.0483   1.0000
  13.250   1.4719   0.05637   0.04893  -0.0906   0.0422   1.0000
  13.500   1.4748   0.05902   0.05166  -0.0899   0.0369   1.0000
  13.750   1.4744   0.06212   0.05479  -0.0894   0.0324   1.0000
  14.000   1.4769   0.06495   0.05773  -0.0890   0.0287   1.0000
  14.250   1.4759   0.06828   0.06111  -0.0887   0.0255   1.0000
  14.500   1.4765   0.07149   0.06444  -0.0885   0.0229   1.0000
  14.750   1.4770   0.07478   0.06782  -0.0884   0.0204   1.0000
  15.000   1.4744   0.07858   0.07169  -0.0886   0.0185   1.0000
  15.250   1.4734   0.08223   0.07547  -0.0888   0.0169   1.0000
  15.500   1.4730   0.08586   0.07924  -0.0891   0.0154   1.0000
  15.750   1.4709   0.08983   0.08330  -0.0897   0.0141   1.0000
  16.000   1.4651   0.09445   0.08805  -0.0905   0.0130   1.0000
  16.250   1.4630   0.09856   0.09231  -0.0913   0.0122   1.0000
  16.500   1.4601   0.10287   0.09677  -0.0923   0.0114   1.0000
  16.750   1.4568   0.10730   0.10135  -0.0935   0.0107   1.0000
  17.000   1.4532   0.11184   0.10601  -0.0949   0.0101   1.0000
  17.250   1.4482   0.11670   0.11098  -0.0966   0.0096   1.0000
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