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EPPLER 397 AIRFOIL (e397-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 397 AIRFOIL (e397-il)
Reynolds number: 500,000
Max Cl/Cd: 125.95 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e397-il-500000-n5.txt
Download as CSV file: xf-e397-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.4739   0.08266   0.07973  -0.0866   0.9871   0.0043
 -13.250  -0.4902   0.07402   0.07098  -0.0936   0.9827   0.0044
 -12.750  -0.5299   0.05838   0.05512  -0.1057   0.9587   0.0042
 -12.500  -0.5435   0.04901   0.04556  -0.1164   0.9463   0.0042
 -12.250  -0.5375   0.04010   0.03640  -0.1305   0.9354   0.0043
 -12.000  -0.5215   0.03207   0.02806  -0.1454   0.9190   0.0043
 -11.750  -0.5146   0.02710   0.02278  -0.1536   0.8958   0.0043
 -11.500  -0.5098   0.02440   0.01980  -0.1569   0.8772   0.0044
 -11.250  -0.4983   0.02284   0.01804  -0.1575   0.8650   0.0045
 -11.000  -0.4834   0.02158   0.01658  -0.1578   0.8547   0.0047
 -10.750  -0.4662   0.02051   0.01534  -0.1578   0.8456   0.0049
 -10.500  -0.4471   0.01951   0.01416  -0.1579   0.8376   0.0051
 -10.250  -0.4274   0.01850   0.01301  -0.1580   0.8297   0.0053
 -10.000  -0.4055   0.01771   0.01208  -0.1581   0.8231   0.0057
  -9.750  -0.3825   0.01699   0.01124  -0.1581   0.8168   0.0061
  -9.500  -0.3586   0.01635   0.01046  -0.1582   0.8107   0.0066
  -9.250  -0.3341   0.01576   0.00974  -0.1583   0.8052   0.0071
  -9.000  -0.3094   0.01514   0.00903  -0.1585   0.7992   0.0079
  -8.750  -0.2839   0.01466   0.00843  -0.1586   0.7940   0.0092
  -8.500  -0.2581   0.01413   0.00784  -0.1588   0.7892   0.0109
  -8.250  -0.2320   0.01366   0.00731  -0.1590   0.7842   0.0133
  -8.000  -0.2055   0.01325   0.00681  -0.1591   0.7794   0.0161
  -7.750  -0.1787   0.01285   0.00637  -0.1593   0.7750   0.0201
  -7.500  -0.1516   0.01249   0.00597  -0.1596   0.7703   0.0245
  -7.250  -0.1244   0.01216   0.00560  -0.1598   0.7660   0.0293
  -7.000  -0.0969   0.01185   0.00524  -0.1600   0.7622   0.0346
  -6.750  -0.0693   0.01154   0.00493  -0.1603   0.7580   0.0412
  -6.500  -0.0416   0.01126   0.00463  -0.1605   0.7537   0.0487
  -6.250  -0.0137   0.01103   0.00436  -0.1608   0.7497   0.0562
  -6.000   0.0144   0.01081   0.00410  -0.1610   0.7463   0.0644
  -5.750   0.0425   0.01057   0.00387  -0.1613   0.7425   0.0736
  -5.500   0.0707   0.01036   0.00366  -0.1616   0.7385   0.0838
  -5.250   0.0990   0.01018   0.00345  -0.1618   0.7348   0.0949
  -5.000   0.1273   0.01003   0.00327  -0.1621   0.7316   0.1064
  -4.750   0.1558   0.00986   0.00312  -0.1623   0.7281   0.1184
  -4.500   0.1842   0.00971   0.00297  -0.1626   0.7243   0.1321
  -4.250   0.2127   0.00957   0.00283  -0.1629   0.7207   0.1464
  -4.000   0.2412   0.00946   0.00271  -0.1631   0.7176   0.1612
  -3.750   0.2698   0.00934   0.00262  -0.1634   0.7144   0.1764
  -3.500   0.2984   0.00924   0.00253  -0.1637   0.7108   0.1910
  -3.250   0.3269   0.00915   0.00245  -0.1639   0.7073   0.2067
  -3.000   0.3554   0.00908   0.00238  -0.1642   0.7041   0.2227
  -2.750   0.3840   0.00903   0.00232  -0.1644   0.7012   0.2380
  -2.500   0.4126   0.00895   0.00228  -0.1646   0.6978   0.2537
  -2.250   0.4412   0.00890   0.00225  -0.1649   0.6944   0.2690
  -2.000   0.4697   0.00885   0.00222  -0.1651   0.6910   0.2846
  -1.750   0.4982   0.00883   0.00220  -0.1653   0.6879   0.2994
  -1.500   0.5267   0.00880   0.00219  -0.1655   0.6849   0.3151
  -1.250   0.5552   0.00876   0.00219  -0.1657   0.6815   0.3304
  -1.000   0.5836   0.00874   0.00220  -0.1659   0.6779   0.3461
  -0.750   0.6120   0.00873   0.00221  -0.1661   0.6746   0.3620
  -0.500   0.6404   0.00874   0.00222  -0.1663   0.6716   0.3782
  -0.250   0.6687   0.00872   0.00226  -0.1665   0.6682   0.3949
   0.000   0.6970   0.00871   0.00230  -0.1666   0.6646   0.4120
   0.250   0.7251   0.00871   0.00234  -0.1668   0.6610   0.4298
   0.500   0.7533   0.00872   0.00238  -0.1669   0.6576   0.4484
   0.750   0.7814   0.00873   0.00245  -0.1671   0.6542   0.4679
   1.000   0.8094   0.00873   0.00252  -0.1672   0.6502   0.4884
   1.250   0.8373   0.00874   0.00258  -0.1673   0.6461   0.5092
   1.500   0.8650   0.00876   0.00265  -0.1673   0.6422   0.5313
   1.750   0.8927   0.00878   0.00274  -0.1674   0.6379   0.5537
   2.000   0.9201   0.00879   0.00284  -0.1674   0.6330   0.5770
   2.250   0.9474   0.00882   0.00293  -0.1673   0.6282   0.6015
   2.500   0.9745   0.00885   0.00304  -0.1672   0.6233   0.6264
   2.750   1.0014   0.00888   0.00315  -0.1671   0.6173   0.6523
   3.000   1.0277   0.00893   0.00325  -0.1669   0.6114   0.6788
   3.250   1.0541   0.00895   0.00339  -0.1666   0.6050   0.7075
   3.500   1.0798   0.00900   0.00352  -0.1662   0.5983   0.7364
   3.750   1.1048   0.00904   0.00365  -0.1657   0.5898   0.7685
   4.000   1.1273   0.00911   0.00378  -0.1646   0.5758   0.8028
   4.250   1.1474   0.00919   0.00392  -0.1630   0.5588   0.8441
   4.500   1.1629   0.00926   0.00404  -0.1603   0.5406   0.9007
   4.750   1.1827   0.00939   0.00416  -0.1587   0.5222   1.0000
   5.000   1.2046   0.00966   0.00437  -0.1577   0.5050   1.0000
   5.250   1.2254   0.00997   0.00460  -0.1565   0.4845   1.0000
   5.500   1.2438   0.01036   0.00489  -0.1548   0.4615   1.0000
   5.750   1.2621   0.01076   0.00521  -0.1532   0.4394   1.0000
   6.000   1.2776   0.01120   0.00556  -0.1510   0.4164   1.0000
   6.250   1.2912   0.01168   0.00594  -0.1484   0.3926   1.0000
   6.500   1.3029   0.01226   0.00640  -0.1456   0.3673   1.0000
   6.750   1.3143   0.01286   0.00691  -0.1429   0.3427   1.0000
   7.000   1.3251   0.01353   0.00746  -0.1401   0.3175   1.0000
   7.250   1.3341   0.01429   0.00810  -0.1371   0.2913   1.0000
   7.500   1.3431   0.01508   0.00879  -0.1342   0.2668   1.0000
   7.750   1.3518   0.01593   0.00953  -0.1314   0.2426   1.0000
   8.000   1.3587   0.01691   0.01039  -0.1284   0.2173   1.0000
   8.250   1.3670   0.01786   0.01126  -0.1258   0.1960   1.0000
   8.500   1.3748   0.01890   0.01221  -0.1232   0.1763   1.0000
   8.750   1.3826   0.01999   0.01322  -0.1208   0.1564   1.0000
   9.000   1.3887   0.02123   0.01437  -0.1182   0.1361   1.0000
   9.250   1.3953   0.02252   0.01557  -0.1159   0.1168   1.0000
   9.500   1.4018   0.02385   0.01684  -0.1137   0.1000   1.0000
   9.750   1.4090   0.02520   0.01813  -0.1117   0.0857   1.0000
  10.000   1.4157   0.02664   0.01952  -0.1097   0.0696   1.0000
  10.250   1.4197   0.02833   0.02111  -0.1076   0.0541   1.0000
  10.500   1.4280   0.02975   0.02252  -0.1059   0.0480   1.0000
  10.750   1.4366   0.03118   0.02398  -0.1044   0.0441   1.0000
  11.000   1.4451   0.03266   0.02549  -0.1029   0.0405   1.0000
  11.250   1.4570   0.03388   0.02679  -0.1018   0.0385   1.0000
  11.500   1.4673   0.03527   0.02823  -0.1007   0.0358   1.0000
  11.750   1.4752   0.03690   0.02989  -0.0994   0.0329   1.0000
  12.000   1.4855   0.03834   0.03139  -0.0983   0.0303   1.0000
  12.250   1.4946   0.03993   0.03301  -0.0973   0.0265   1.0000
  12.500   1.5023   0.04168   0.03477  -0.0962   0.0224   1.0000
  12.750   1.5089   0.04358   0.03669  -0.0952   0.0186   1.0000
  13.000   1.5149   0.04560   0.03872  -0.0942   0.0158   1.0000
  13.250   1.5211   0.04764   0.04082  -0.0933   0.0139   1.0000
  13.500   1.5262   0.04984   0.04306  -0.0924   0.0122   1.0000
  13.750   1.5322   0.05200   0.04530  -0.0916   0.0108   1.0000
  14.000   1.5359   0.05447   0.04782  -0.0909   0.0096   1.0000
  14.250   1.5417   0.05674   0.05017  -0.0903   0.0085   1.0000
  14.500   1.5454   0.05930   0.05281  -0.0898   0.0075   1.0000
  14.750   1.5495   0.06189   0.05548  -0.0893   0.0068   1.0000
  15.000   1.5538   0.06449   0.05817  -0.0890   0.0062   1.0000
  15.250   1.5565   0.06736   0.06111  -0.0887   0.0057   1.0000
  15.500   1.5581   0.07042   0.06425  -0.0885   0.0052   1.0000
  15.750   1.5610   0.07338   0.06732  -0.0885   0.0049   1.0000
  16.000   1.5630   0.07652   0.07055  -0.0885   0.0045   1.0000
  16.250   1.5640   0.07985   0.07399  -0.0887   0.0042   1.0000
  16.500   1.5641   0.08336   0.07758  -0.0890   0.0040   1.0000
  16.750   1.5624   0.08722   0.08155  -0.0895   0.0037   1.0000
  17.000   1.5621   0.09093   0.08538  -0.0901   0.0035   1.0000
  17.250   1.5611   0.09481   0.08938  -0.0908   0.0034   1.0000
  17.500   1.5600   0.09877   0.09345  -0.0916   0.0032   1.0000
  17.750   1.5578   0.10293   0.09772  -0.0926   0.0030   1.0000
  18.000   1.5551   0.10723   0.10214  -0.0938   0.0029   1.0000
  18.250   1.5517   0.11171   0.10673  -0.0952   0.0028   1.0000
  18.500   1.5474   0.11640   0.11154  -0.0968   0.0027   1.0000
  18.750   1.5419   0.12137   0.11662  -0.0987   0.0026   1.0000
  19.000   1.5351   0.12661   0.12198  -0.1008   0.0025   1.0000
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