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EPPLER 396 AIRFOIL (e396-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 396 AIRFOIL (e396-il)
Reynolds number: 500,000
Max Cl/Cd: 135.14 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e396-il-500000.txt
Download as CSV file: xf-e396-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.4096   0.07055   0.06805  -0.0911   0.9861   0.0084
 -11.500  -0.4279   0.05951   0.05683  -0.1025   0.9796   0.0083
 -11.250  -0.4287   0.05165   0.04883  -0.1123   0.9722   0.0082
 -11.000  -0.4265   0.04498   0.04199  -0.1210   0.9614   0.0081
 -10.750  -0.4264   0.03466   0.03133  -0.1379   0.9479   0.0082
 -10.500  -0.4057   0.02721   0.02339  -0.1541   0.9338   0.0084
 -10.250  -0.3846   0.02430   0.02019  -0.1586   0.9220   0.0086
 -10.000  -0.3626   0.02248   0.01817  -0.1608   0.9115   0.0089
  -9.750  -0.3391   0.02114   0.01664  -0.1622   0.9020   0.0093
  -9.500  -0.3192   0.01992   0.01523  -0.1624   0.8916   0.0096
  -9.250  -0.2970   0.01883   0.01395  -0.1628   0.8830   0.0100
  -9.000  -0.2741   0.01780   0.01273  -0.1630   0.8750   0.0104
  -8.750  -0.2505   0.01696   0.01172  -0.1631   0.8673   0.0110
  -8.500  -0.2274   0.01577   0.01033  -0.1634   0.8602   0.0120
  -8.250  -0.2025   0.01510   0.00959  -0.1636   0.8535   0.0133
  -8.000  -0.1762   0.01461   0.00899  -0.1637   0.8473   0.0149
  -7.750  -0.1507   0.01369   0.00794  -0.1640   0.8414   0.0177
  -7.500  -0.1241   0.01329   0.00745  -0.1640   0.8352   0.0210
  -7.250  -0.0968   0.01264   0.00672  -0.1644   0.8302   0.0272
  -7.000  -0.0701   0.01218   0.00623  -0.1646   0.8246   0.0339
  -6.750  -0.0427   0.01181   0.00580  -0.1648   0.8192   0.0405
  -6.500  -0.0142   0.01160   0.00551  -0.1651   0.8147   0.0466
  -6.250   0.0129   0.01123   0.00515  -0.1652   0.8094   0.0551
  -6.000   0.0409   0.01095   0.00483  -0.1655   0.8045   0.0641
  -5.750   0.0696   0.01076   0.00455  -0.1658   0.8002   0.0736
  -5.500   0.0972   0.01051   0.00431  -0.1659   0.7953   0.0847
  -5.250   0.1254   0.01027   0.00406  -0.1661   0.7906   0.0979
  -5.000   0.1543   0.01009   0.00385  -0.1665   0.7865   0.1120
  -4.750   0.1823   0.00990   0.00367  -0.1667   0.7820   0.1266
  -4.500   0.2106   0.00973   0.00350  -0.1669   0.7774   0.1422
  -4.250   0.2393   0.00957   0.00335  -0.1672   0.7734   0.1597
  -4.000   0.2679   0.00945   0.00324  -0.1674   0.7693   0.1769
  -3.750   0.2961   0.00933   0.00314  -0.1676   0.7647   0.1958
  -3.500   0.3247   0.00924   0.00304  -0.1678   0.7606   0.2148
  -3.250   0.3539   0.00917   0.00297  -0.1682   0.7569   0.2341
  -3.000   0.3819   0.00907   0.00292  -0.1683   0.7525   0.2525
  -2.750   0.4103   0.00900   0.00286  -0.1685   0.7482   0.2723
  -2.500   0.4392   0.00895   0.00280  -0.1687   0.7444   0.2913
  -2.250   0.4678   0.00890   0.00278  -0.1690   0.7405   0.3113
  -2.000   0.4959   0.00885   0.00276  -0.1691   0.7360   0.3308
  -1.750   0.5245   0.00880   0.00273  -0.1693   0.7319   0.3515
  -1.500   0.5537   0.00879   0.00272  -0.1696   0.7282   0.3730
  -1.250   0.5815   0.00874   0.00274  -0.1697   0.7238   0.3952
  -1.000   0.6098   0.00870   0.00274  -0.1698   0.7194   0.4181
  -0.750   0.6385   0.00868   0.00275  -0.1700   0.7155   0.4426
  -0.250   0.6947   0.00863   0.00283  -0.1703   0.7067   0.4959
   0.000   0.7230   0.00861   0.00286  -0.1704   0.7025   0.5244
   0.250   0.7518   0.00863   0.00291  -0.1707   0.6986   0.5545
   0.500   0.7791   0.00859   0.00298  -0.1706   0.6938   0.5854
   0.750   0.8070   0.00857   0.00304  -0.1706   0.6892   0.6181
   1.000   0.8354   0.00859   0.00310  -0.1708   0.6851   0.6519
   1.250   0.8622   0.00856   0.00321  -0.1706   0.6802   0.6872
   1.500   0.8892   0.00854   0.00328  -0.1704   0.6753   0.7244
   1.750   0.9163   0.00855   0.00336  -0.1702   0.6709   0.7633
   2.000   0.9413   0.00852   0.00347  -0.1695   0.6656   0.8048
   2.250   0.9647   0.00847   0.00354  -0.1685   0.6603   0.8518
   2.500   0.9845   0.00841   0.00356  -0.1665   0.6556   0.9141
   2.750   1.0105   0.00834   0.00358  -0.1660   0.6496   1.0000
   3.000   1.0384   0.00843   0.00363  -0.1661   0.6439   1.0000
   3.250   1.0659   0.00853   0.00372  -0.1662   0.6378   1.0000
   3.500   1.0927   0.00861   0.00380  -0.1660   0.6309   1.0000
   3.750   1.1197   0.00872   0.00389  -0.1660   0.6242   1.0000
   4.000   1.1461   0.00881   0.00399  -0.1657   0.6169   1.0000
   4.250   1.1726   0.00893   0.00410  -0.1655   0.6098   1.0000
   4.500   1.1983   0.00904   0.00421  -0.1652   0.6015   1.0000
   4.750   1.2239   0.00916   0.00434  -0.1648   0.5932   1.0000
   5.000   1.2493   0.00931   0.00447  -0.1644   0.5850   1.0000
   5.250   1.2743   0.00944   0.00464  -0.1640   0.5758   1.0000
   5.500   1.2987   0.00961   0.00480  -0.1634   0.5662   1.0000
   5.750   1.3223   0.00980   0.00497  -0.1626   0.5553   1.0000
   6.000   1.3458   0.00998   0.00516  -0.1619   0.5439   1.0000
   6.250   1.3687   0.01018   0.00539  -0.1610   0.5321   1.0000
   6.500   1.3908   0.01042   0.00562  -0.1600   0.5196   1.0000
   6.750   1.4115   0.01068   0.00587  -0.1587   0.5048   1.0000
   7.000   1.4309   0.01099   0.00614  -0.1572   0.4884   1.0000
   7.250   1.4490   0.01134   0.00646  -0.1555   0.4712   1.0000
   7.500   1.4645   0.01174   0.00682  -0.1533   0.4516   1.0000
   7.750   1.4776   0.01217   0.00720  -0.1506   0.4306   1.0000
   8.000   1.4875   0.01273   0.00766  -0.1475   0.4070   1.0000
   8.250   1.4952   0.01340   0.00823  -0.1440   0.3802   1.0000
   8.500   1.5015   0.01419   0.00890  -0.1404   0.3512   1.0000
   8.750   1.5065   0.01510   0.00967  -0.1369   0.3219   1.0000
   9.000   1.5104   0.01613   0.01057  -0.1333   0.2929   1.0000
   9.250   1.5131   0.01729   0.01159  -0.1297   0.2638   1.0000
   9.500   1.5151   0.01858   0.01276  -0.1262   0.2358   1.0000
   9.750   1.5168   0.01999   0.01403  -0.1230   0.2094   1.0000
  10.000   1.5200   0.02139   0.01533  -0.1201   0.1852   1.0000
  10.250   1.5232   0.02289   0.01673  -0.1174   0.1636   1.0000
  10.500   1.5256   0.02451   0.01825  -0.1148   0.1428   1.0000
  10.750   1.5289   0.02615   0.01982  -0.1124   0.1244   1.0000
  11.000   1.5318   0.02789   0.02149  -0.1102   0.1066   1.0000
  11.250   1.5343   0.02974   0.02327  -0.1080   0.0911   1.0000
  11.500   1.5365   0.03168   0.02514  -0.1060   0.0770   1.0000
  11.750   1.5391   0.03367   0.02709  -0.1042   0.0645   1.0000
  12.000   1.5415   0.03574   0.02914  -0.1025   0.0534   1.0000
  12.250   1.5449   0.03779   0.03118  -0.1009   0.0449   1.0000
  12.500   1.5481   0.03993   0.03333  -0.0995   0.0375   1.0000
  12.750   1.5506   0.04222   0.03562  -0.0982   0.0317   1.0000
  13.000   1.5534   0.04453   0.03795  -0.0970   0.0271   1.0000
  13.250   1.5561   0.04692   0.04039  -0.0959   0.0231   1.0000
  13.500   1.5583   0.04945   0.04295  -0.0949   0.0200   1.0000
  13.750   1.5591   0.05221   0.04577  -0.0940   0.0172   1.0000
  14.000   1.5621   0.05478   0.04841  -0.0933   0.0151   1.0000
  14.250   1.5577   0.05834   0.05202  -0.0925   0.0131   1.0000
  14.500   1.5608   0.06107   0.05485  -0.0920   0.0118   1.0000
  14.750   1.5626   0.06401   0.05788  -0.0916   0.0106   1.0000
  15.000   1.5569   0.06803   0.06199  -0.0914   0.0094   1.0000
  15.250   1.5548   0.07168   0.06576  -0.0913   0.0086   1.0000
  15.500   1.5562   0.07491   0.06910  -0.0913   0.0079   1.0000
  15.750   1.5567   0.07835   0.07262  -0.0915   0.0073   1.0000
  16.000   1.5531   0.08243   0.07679  -0.0919   0.0067   1.0000
  16.250   1.5401   0.08809   0.08257  -0.0926   0.0063   1.0000
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