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EPPLER 49 AIRFOIL (e49-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 49 AIRFOIL (e49-il)
Reynolds number: 1,000,000
Max Cl/Cd: 123.08 at α=0.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e49-il-1000000-n5.txt
Download as CSV file: xf-e49-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.0018   0.10088   0.09885  -0.1315   0.9302   0.0037
 -10.750   0.0042   0.09884   0.09680  -0.1316   0.9289   0.0044
 -10.500   0.0106   0.09647   0.09444  -0.1320   0.9279   0.0046
 -10.250   0.0174   0.09396   0.09194  -0.1328   0.9271   0.0047
  -7.000   0.0414   0.07014   0.06825  -0.1237   0.9006   0.0059
  -6.750   0.0570   0.06662   0.06474  -0.1270   0.8988   0.0059
  -6.500   0.0768   0.06274   0.06084  -0.1314   0.8976   0.0059
  -6.250   0.0949   0.05577   0.05384  -0.1384   0.8965   0.0052
  -6.000   0.1254   0.05052   0.04855  -0.1463   0.8959   0.0050
  -5.500   0.2290   0.03399   0.03171  -0.1737   0.8952   0.0068
  -5.250   0.2595   0.03261   0.03028  -0.1765   0.8949   0.0074
  -5.000   0.2590   0.03238   0.03003  -0.1721   0.8889   0.0078
  -4.750   0.2841   0.03094   0.02853  -0.1735   0.8868   0.0088
  -4.500   0.3214   0.02814   0.02556  -0.1777   0.8860   0.0099
  -4.250   0.3604   0.02535   0.02257  -0.1818   0.8856   0.0109
  -4.000   0.4034   0.02200   0.01890  -0.1862   0.8856   0.0103
  -3.750   0.4436   0.01917   0.01571  -0.1894   0.8855   0.0097
  -3.500   0.4807   0.01692   0.01307  -0.1917   0.8852   0.0091
  -3.250   0.5154   0.01513   0.01094  -0.1932   0.8847   0.0087
  -3.000   0.5481   0.01380   0.00929  -0.1943   0.8841   0.0084
  -2.250   0.3910   0.00868   0.00215  -0.1243   0.9010   0.0368
  -1.750   0.5195   0.02327   0.02054  -0.2608   0.9282   0.0085
  -0.750   0.8007   0.01030   0.00543  -0.1960   0.8641   0.0195
   0.250   0.9037   0.00975   0.00482  -0.1949   0.8390   0.0171
   0.750   0.9994   0.00812   0.00327  -0.2039   0.7760   0.2657
   1.000   1.0000   0.00882   0.00364  -0.1982   0.7015   0.3241
   1.250   1.0111   0.00917   0.00407  -0.1950   0.6689   0.4512
   1.750   1.0406   0.00910   0.00488  -0.1901   0.6229   1.0000
   2.000   1.0392   0.01019   0.00548  -0.1844   0.5299   1.0000
   2.250   1.0336   0.01207   0.00628  -0.1783   0.3307   1.0000
   2.750   1.0508   0.01516   0.00776  -0.1721   0.0063   1.0000
   3.000   1.0736   0.01542   0.00797  -0.1714   0.0049   1.0000
   3.250   1.0965   0.01568   0.00820  -0.1708   0.0028   1.0000
   3.500   1.1190   0.01596   0.00851  -0.1700   0.0022   1.0000
   3.750   1.1413   0.01627   0.00885  -0.1692   0.0021   1.0000
   4.000   1.1634   0.01660   0.00927  -0.1684   0.0022   1.0000
   4.250   1.1849   0.01698   0.00970  -0.1675   0.0022   1.0000
   4.500   1.2058   0.01742   0.01018  -0.1664   0.0023   1.0000
   4.750   1.2260   0.01790   0.01072  -0.1652   0.0025   1.0000
   5.000   1.2457   0.01843   0.01129  -0.1640   0.0027   1.0000
   5.250   1.2649   0.01901   0.01193  -0.1626   0.0030   1.0000
   5.500   1.2832   0.01971   0.01270  -0.1610   0.0036   1.0000
   5.750   1.2997   0.02061   0.01373  -0.1590   0.0046   1.0000
   6.000   1.3139   0.02171   0.01496  -0.1565   0.0058   1.0000
   9.000   1.5268   0.03973   0.03423  -0.1397   0.0033   1.0000
   9.250   1.5350   0.04175   0.03640  -0.1372   0.0030   1.0000
   9.500   1.5406   0.04394   0.03877  -0.1344   0.0029   1.0000
   9.750   1.5432   0.04634   0.04134  -0.1313   0.0027   1.0000
  10.000   1.5438   0.04899   0.04417  -0.1281   0.0026   1.0000
  10.250   1.5415   0.05197   0.04733  -0.1247   0.0024   1.0000
  10.500   1.5362   0.05529   0.05085  -0.1211   0.0023   1.0000
  10.750   1.5265   0.05906   0.05484  -0.1174   0.0023   1.0000
  11.000   1.5134   0.06322   0.05922  -0.1137   0.0022   1.0000
  11.250   1.4977   0.06764   0.06387  -0.1103   0.0021   1.0000
  11.500   1.4795   0.07242   0.06886  -0.1073   0.0021   1.0000
  11.750   1.4609   0.07734   0.07399  -0.1049   0.0021   1.0000
  12.000   1.4420   0.08249   0.07934  -0.1032   0.0020   1.0000
  12.250   1.4223   0.08804   0.08507  -0.1023   0.0020   1.0000
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