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EPPLER 49 AIRFOIL (e49-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 49 AIRFOIL (e49-il)
Reynolds number: 200,000
Max Cl/Cd: 65 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e49-il-200000-n5.txt
Download as CSV file: xf-e49-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 49 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2129   0.10853   0.10500  -0.0611   0.9323   0.0167
  -7.750  -0.2161   0.10659   0.10309  -0.0599   0.9290   0.0167
  -7.500  -0.2117   0.10395   0.10047  -0.0609   0.9262   0.0167
  -7.250  -0.1968   0.10045   0.09688  -0.0646   0.9242   0.0167
  -7.000  -0.1962   0.09781   0.09427  -0.0643   0.9181   0.0167
  -6.750  -0.1870   0.09461   0.09108  -0.0663   0.9143   0.0167
  -6.500  -0.1708   0.09089   0.08736  -0.0700   0.9119   0.0167
  -6.250  -0.1493   0.08680   0.08326  -0.0749   0.9101   0.0167
  -6.000  -0.1342   0.08328   0.07973  -0.0780   0.9069   0.0167
  -5.750  -0.1263   0.08021   0.07667  -0.0790   0.9015   0.0167
  -5.500  -0.1027   0.07608   0.07251  -0.0838   0.8986   0.0166
  -5.250  -0.0738   0.07160   0.06798  -0.0897   0.8967   0.0165
  -5.000  -0.0435   0.06701   0.06335  -0.0956   0.8954   0.0162
  -4.750  -0.0091   0.06225   0.05853  -0.1024   0.8944   0.0155
  -4.500   0.0140   0.05856   0.05477  -0.1062   0.8892   0.0151
  -4.250   0.0577   0.05379   0.04987  -0.1145   0.8868   0.0150
  -3.000   0.2978   0.03489   0.02958  -0.1488   0.8821   0.0226
  -2.750   0.3440   0.03191   0.02604  -0.1528   0.8815   0.0194
  -2.250   0.4206   0.02934   0.02254  -0.1567   0.8795   0.0173
  -2.000   0.4580   0.02785   0.02068  -0.1589   0.8788   0.0174
  -1.750   0.4760   0.02675   0.01932  -0.1573   0.8720   0.0182
  -1.500   0.5058   0.02590   0.01831  -0.1579   0.8690   0.0199
  -1.250   0.5376   0.02531   0.01758  -0.1589   0.8667   0.0244
  -1.000   0.5702   0.02479   0.01696  -0.1600   0.8649   0.0301
  -0.750   0.6040   0.02421   0.01635  -0.1612   0.8635   0.0293
  -0.500   0.6223   0.02403   0.01616  -0.1596   0.8562   0.0289
  -0.250   0.6505   0.02371   0.01582  -0.1599   0.8520   0.0285
   0.000   0.6828   0.02336   0.01545  -0.1609   0.8495   0.0290
   0.250   0.7165   0.02301   0.01503  -0.1621   0.8476   0.0295
   0.750   0.7655   0.02266   0.01463  -0.1610   0.8346   0.0357
   1.000   0.7992   0.02072   0.01465  -0.1626   0.8323   1.0000
   1.250   0.8193   0.02067   0.01453  -0.1611   0.8215   1.0000
   1.500   0.8518   0.02022   0.01403  -0.1618   0.8167   1.0000
   1.750   0.8713   0.02029   0.01409  -0.1603   0.8056   1.0000
   2.000   0.9013   0.01997   0.01375  -0.1607   0.8008   1.0000
   2.250   0.9218   0.02007   0.01386  -0.1594   0.7894   1.0000
   2.500   0.9528   0.01971   0.01358  -0.1600   0.7836   1.0000
   3.000   1.0083   0.01926   0.01314  -0.1599   0.7624   1.0000
   3.250   1.0462   0.01849   0.01235  -0.1616   0.7494   1.0000
   3.500   1.0931   0.01739   0.01121  -0.1649   0.7316   1.0000
   3.750   1.1355   0.01747   0.00905  -0.1666   0.4209   1.0000
   4.000   1.1226   0.02000   0.01041  -0.1598   0.2439   1.0000
   4.250   1.1406   0.02064   0.01103  -0.1584   0.2148   1.0000
   4.500   1.1508   0.02203   0.01192  -0.1559   0.1332   1.0000
   4.750   1.1547   0.02417   0.01334  -0.1524   0.0071   1.0000
   5.000   1.1745   0.02472   0.01397  -0.1512   0.0063   1.0000
   5.250   1.1938   0.02533   0.01468  -0.1499   0.0058   1.0000
   5.500   1.2125   0.02600   0.01548  -0.1486   0.0056   1.0000
   5.750   1.2304   0.02676   0.01639  -0.1471   0.0054   1.0000
   6.000   1.2475   0.02758   0.01736  -0.1455   0.0054   1.0000
   6.250   1.2637   0.02852   0.01847  -0.1437   0.0053   1.0000
   6.500   1.2785   0.02962   0.01983  -0.1418   0.0052   1.0000
   6.750   1.2919   0.03083   0.02120  -0.1397   0.0052   1.0000
   7.000   1.3035   0.03219   0.02271  -0.1373   0.0053   1.0000
   7.250   1.3132   0.03370   0.02437  -0.1348   0.0053   1.0000
   7.500   1.3223   0.03532   0.02612  -0.1322   0.0054   1.0000
   7.750   1.3316   0.03707   0.02800  -0.1297   0.0055   1.0000
   8.000   1.3421   0.03891   0.02996  -0.1275   0.0056   1.0000
   8.250   1.3549   0.04079   0.03197  -0.1256   0.0057   1.0000
   8.500   1.3709   0.04275   0.03407  -0.1242   0.0058   1.0000
   8.750   1.3903   0.04483   0.03632  -0.1232   0.0059   1.0000
   9.000   1.4115   0.04712   0.03882  -0.1225   0.0061   1.0000
   9.250   1.4315   0.04968   0.04164  -0.1216   0.0062   1.0000
   9.500   1.4474   0.05255   0.04481  -0.1203   0.0063   1.0000
   9.750   1.4575   0.05566   0.04823  -0.1184   0.0065   1.0000
  10.000   1.4621   0.05900   0.05191  -0.1159   0.0066   1.0000
  10.250   1.4614   0.06254   0.05578  -0.1131   0.0067   1.0000
  10.500   1.4566   0.06628   0.05982  -0.1101   0.0068   1.0000
  10.750   1.4483   0.07025   0.06410  -0.1071   0.0069   1.0000
  11.000   1.4372   0.07443   0.06858  -0.1043   0.0070   1.0000
  11.250   1.4238   0.07883   0.07326  -0.1019   0.0070   1.0000
  11.500   1.4088   0.08349   0.07818  -0.0999   0.0071   1.0000
  11.750   1.3926   0.08839   0.08334  -0.0986   0.0071   1.0000
  12.000   1.3757   0.09358   0.08877  -0.0979   0.0072   1.0000
  12.250   1.3583   0.09911   0.09453  -0.0980   0.0072   1.0000
  12.500   1.3410   0.10490   0.10053  -0.0989   0.0073   1.0000
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