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EPPLER 397 AIRFOIL (e397-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 397 AIRFOIL (e397-il)
Reynolds number: 200,000
Max Cl/Cd: 89.27 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e397-il-200000-n5.txt
Download as CSV file: xf-e397-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.3314   0.09818   0.09460  -0.0767   0.9842   0.0120
 -12.000  -0.3779   0.08216   0.07846  -0.0862   0.9767   0.0117
 -11.750  -0.4003   0.07192   0.06811  -0.0943   0.9679   0.0114
 -11.500  -0.4191   0.06248   0.05850  -0.1028   0.9579   0.0112
 -11.250  -0.4306   0.05443   0.05028  -0.1111   0.9468   0.0111
 -11.000  -0.4349   0.04668   0.04228  -0.1209   0.9364   0.0112
 -10.750  -0.4300   0.03993   0.03525  -0.1311   0.9262   0.0114
 -10.500  -0.4215   0.03445   0.02944  -0.1402   0.9141   0.0116
 -10.250  -0.4093   0.03061   0.02526  -0.1467   0.9016   0.0120
 -10.000  -0.3945   0.02819   0.02262  -0.1495   0.8914   0.0124
  -9.750  -0.3731   0.02629   0.02052  -0.1520   0.8843   0.0131
  -9.500  -0.3554   0.02482   0.01886  -0.1528   0.8754   0.0140
  -9.250  -0.3318   0.02339   0.01715  -0.1541   0.8692   0.0153
  -9.000  -0.3116   0.02231   0.01596  -0.1545   0.8613   0.0169
  -8.750  -0.2867   0.02129   0.01472  -0.1552   0.8554   0.0193
  -8.500  -0.2638   0.02031   0.01364  -0.1557   0.8492   0.0217
  -8.250  -0.2396   0.01938   0.01255  -0.1560   0.8432   0.0248
  -8.000  -0.2123   0.01868   0.01168  -0.1567   0.8386   0.0294
  -7.750  -0.1884   0.01802   0.01097  -0.1568   0.8323   0.0343
  -7.500  -0.1620   0.01741   0.01027  -0.1572   0.8271   0.0403
  -7.250  -0.1340   0.01686   0.00960  -0.1578   0.8230   0.0472
  -6.750  -0.0817   0.01595   0.00854  -0.1581   0.8126   0.0622
  -6.500  -0.0533   0.01551   0.00801  -0.1587   0.8086   0.0709
  -6.250  -0.0267   0.01516   0.00760  -0.1588   0.8037   0.0806
  -6.000   0.0005   0.01484   0.00721  -0.1590   0.7991   0.0913
  -5.750   0.0288   0.01452   0.00682  -0.1594   0.7952   0.1033
  -5.500   0.0572   0.01423   0.00649  -0.1598   0.7914   0.1164
  -5.250   0.0841   0.01399   0.00623  -0.1599   0.7866   0.1301
  -5.000   0.1121   0.01376   0.00597  -0.1601   0.7825   0.1453
  -4.750   0.1409   0.01356   0.00571  -0.1605   0.7790   0.1615
  -4.500   0.1690   0.01339   0.00552  -0.1608   0.7752   0.1778
  -4.250   0.1964   0.01324   0.00536  -0.1609   0.7707   0.1944
  -4.000   0.2246   0.01310   0.00521  -0.1611   0.7669   0.2117
  -3.750   0.2536   0.01297   0.00506  -0.1615   0.7637   0.2299
  -3.500   0.2818   0.01288   0.00495  -0.1617   0.7600   0.2474
  -3.250   0.3092   0.01280   0.00488  -0.1618   0.7557   0.2648
  -3.000   0.3374   0.01273   0.00480  -0.1620   0.7520   0.2823
  -2.750   0.3663   0.01267   0.00470  -0.1623   0.7489   0.3000
  -2.500   0.3949   0.01263   0.00464  -0.1625   0.7455   0.3175
  -2.250   0.4220   0.01260   0.00464  -0.1625   0.7413   0.3343
  -2.000   0.4500   0.01256   0.00462  -0.1626   0.7376   0.3519
  -1.750   0.4786   0.01253   0.00458  -0.1628   0.7343   0.3697
  -1.500   0.5078   0.01250   0.00455  -0.1632   0.7314   0.3881
  -1.250   0.5344   0.01251   0.00461  -0.1631   0.7272   0.4063
  -1.000   0.5619   0.01251   0.00465  -0.1631   0.7233   0.4252
  -0.750   0.5903   0.01251   0.00466  -0.1633   0.7199   0.4451
  -0.500   0.6194   0.01250   0.00467  -0.1636   0.7170   0.4652
  -0.250   0.6460   0.01253   0.00478  -0.1634   0.7130   0.4862
   0.250   0.7008   0.01256   0.00493  -0.1634   0.7054   0.5308
   0.500   0.7295   0.01257   0.00498  -0.1636   0.7024   0.5554
   0.750   0.7559   0.01261   0.00512  -0.1634   0.6984   0.5796
   1.000   0.7820   0.01266   0.00526  -0.1631   0.6942   0.6054
   1.250   0.8090   0.01268   0.00536  -0.1629   0.6904   0.6321
   1.500   0.8368   0.01270   0.00543  -0.1629   0.6872   0.6604
   1.750   0.8619   0.01276   0.00562  -0.1624   0.6829   0.6890
   2.000   0.8866   0.01280   0.00578  -0.1617   0.6783   0.7194
   2.250   0.9120   0.01282   0.00589  -0.1612   0.6743   0.7519
   2.500   0.9376   0.01282   0.00596  -0.1605   0.6707   0.7874
   2.750   0.9578   0.01286   0.00616  -0.1589   0.6653   0.8272
   3.000   0.9779   0.01282   0.00623  -0.1571   0.6604   0.8789
   3.250   1.0054   0.01271   0.00616  -0.1568   0.6563   1.0000
   3.500   1.0302   0.01289   0.00639  -0.1564   0.6502   1.0000
   3.750   1.0572   0.01301   0.00651  -0.1564   0.6445   1.0000
   4.000   1.0847   0.01312   0.00662  -0.1564   0.6390   1.0000
   4.250   1.1091   0.01327   0.00683  -0.1559   0.6319   1.0000
   4.500   1.1371   0.01337   0.00689  -0.1560   0.6261   1.0000
   4.750   1.1600   0.01355   0.00715  -0.1552   0.6181   1.0000
   5.000   1.1868   0.01364   0.00724  -0.1550   0.6110   1.0000
   5.250   1.2089   0.01382   0.00748  -0.1540   0.6010   1.0000
   5.500   1.2318   0.01395   0.00764  -0.1531   0.5900   1.0000
   5.750   1.2533   0.01409   0.00779  -0.1519   0.5764   1.0000
   6.000   1.2730   0.01426   0.00795  -0.1503   0.5597   1.0000
   6.250   1.2916   0.01449   0.00815  -0.1486   0.5412   1.0000
   6.500   1.3092   0.01477   0.00837  -0.1467   0.5215   1.0000
   6.750   1.3262   0.01510   0.00869  -0.1448   0.5026   1.0000
   7.000   1.3414   0.01546   0.00904  -0.1425   0.4847   1.0000
   7.250   1.3545   0.01590   0.00944  -0.1399   0.4656   1.0000
   7.500   1.3656   0.01643   0.00992  -0.1371   0.4451   1.0000
   7.750   1.3754   0.01705   0.01048  -0.1341   0.4225   1.0000
   8.000   1.3821   0.01782   0.01118  -0.1308   0.3986   1.0000
   8.250   1.3856   0.01878   0.01203  -0.1271   0.3714   1.0000
   8.500   1.3879   0.01988   0.01302  -0.1235   0.3440   1.0000
   8.750   1.3900   0.02110   0.01415  -0.1201   0.3181   1.0000
   9.000   1.3908   0.02250   0.01543  -0.1167   0.2921   1.0000
   9.250   1.3922   0.02398   0.01682  -0.1137   0.2675   1.0000
   9.500   1.3957   0.02544   0.01824  -0.1111   0.2464   1.0000
   9.750   1.3997   0.02695   0.01970  -0.1087   0.2267   1.0000
  10.000   1.4021   0.02864   0.02133  -0.1063   0.2068   1.0000
  10.250   1.4044   0.03044   0.02306  -0.1041   0.1848   1.0000
  10.500   1.4050   0.03245   0.02497  -0.1019   0.1633   1.0000
  10.750   1.4069   0.03443   0.02688  -0.0999   0.1417   1.0000
  11.000   1.4083   0.03655   0.02891  -0.0981   0.1223   1.0000
  11.250   1.4110   0.03862   0.03093  -0.0965   0.1052   1.0000
  11.500   1.4141   0.04072   0.03302  -0.0950   0.0907   1.0000
  11.750   1.4177   0.04285   0.03513  -0.0936   0.0768   1.0000
  12.000   1.4205   0.04512   0.03737  -0.0923   0.0638   1.0000
  12.250   1.4232   0.04747   0.03969  -0.0912   0.0561   1.0000
  12.500   1.4252   0.04996   0.04218  -0.0901   0.0506   1.0000
  12.750   1.4297   0.05226   0.04456  -0.0892   0.0463   1.0000
  13.000   1.4315   0.05489   0.04725  -0.0883   0.0425   1.0000
  13.250   1.4345   0.05748   0.04994  -0.0876   0.0391   1.0000
  13.500   1.4402   0.05980   0.05240  -0.0870   0.0353   1.0000
  13.750   1.4409   0.06278   0.05543  -0.0865   0.0321   1.0000
  14.000   1.4477   0.06506   0.05785  -0.0861   0.0285   1.0000
  14.250   1.4503   0.06791   0.06074  -0.0858   0.0254   1.0000
  14.500   1.4545   0.07062   0.06356  -0.0856   0.0223   1.0000
  14.750   1.4557   0.07378   0.06676  -0.0855   0.0201   1.0000
  15.000   1.4572   0.07697   0.07008  -0.0854   0.0182   1.0000
  15.250   1.4568   0.08048   0.07365  -0.0856   0.0165   1.0000
  15.500   1.4553   0.08422   0.07752  -0.0859   0.0152   1.0000
  15.750   1.4544   0.08797   0.08139  -0.0863   0.0139   1.0000
  16.000   1.4517   0.09205   0.08557  -0.0869   0.0129   1.0000
  16.250   1.4478   0.09640   0.09003  -0.0877   0.0121   1.0000
  16.500   1.4451   0.10061   0.09441  -0.0886   0.0114   1.0000
  16.750   1.4417   0.10502   0.09895  -0.0897   0.0108   1.0000
  17.000   1.4377   0.10959   0.10365  -0.0910   0.0103   1.0000
  17.250   1.4327   0.11439   0.10858  -0.0926   0.0099   1.0000
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