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E211 (10.96%) (e211-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: E211 (10.96%) (e211-il)
Reynolds number: 50,000
Max Cl/Cd: 37.86 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e211-il-50000.txt
Download as CSV file: xf-e211-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E211  (10.96%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4156   0.11768   0.11057  -0.0236   1.0000   0.2467
  -9.250  -0.3987   0.11293   0.10582  -0.0225   1.0000   0.2539
  -9.000  -0.4238   0.11275   0.10581  -0.0232   1.0000   0.2625
  -8.750  -0.3965   0.10733   0.10034  -0.0215   1.0000   0.2726
  -8.500  -0.3976   0.10443   0.09752  -0.0209   1.0000   0.2814
  -8.250  -0.4218   0.10409   0.09735  -0.0205   1.0000   0.2921
  -8.000  -0.4043   0.09994   0.09318  -0.0189   1.0000   0.3056
  -7.750  -0.3950   0.09653   0.08980  -0.0174   1.0000   0.3186
  -7.500  -0.3906   0.09350   0.08683  -0.0160   1.0000   0.3312
  -6.500  -0.5140   0.06381   0.05724  -0.0457   1.0000   0.1437
  -6.250  -0.5086   0.05723   0.05034  -0.0480   1.0000   0.1280
  -6.000  -0.4999   0.05098   0.04359  -0.0503   1.0000   0.1181
  -5.750  -0.4839   0.04652   0.03860  -0.0513   1.0000   0.1137
  -5.500  -0.4658   0.04274   0.03437  -0.0518   1.0000   0.1132
  -5.250  -0.4445   0.03930   0.03036  -0.0523   1.0000   0.1139
  -5.000  -0.4208   0.03627   0.02675  -0.0525   1.0000   0.1150
  -4.750  -0.3961   0.03345   0.02348  -0.0523   1.0000   0.1167
  -4.500  -0.3726   0.03120   0.02111  -0.0518   1.0000   0.1212
  -4.250  -0.3472   0.02934   0.01887  -0.0512   1.0000   0.1312
  -4.000  -0.3236   0.02764   0.01721  -0.0503   1.0000   0.1477
  -3.750  -0.3003   0.02595   0.01564  -0.0493   1.0000   0.1775
  -3.500  -0.2776   0.02404   0.01426  -0.0487   1.0000   0.2573
  -3.250  -0.2564   0.02173   0.01351  -0.0472   1.0000   0.4517
  -3.000  -0.2519   0.02207   0.01454  -0.0402   1.0000   0.6202
  -2.750  -0.2504   0.02251   0.01510  -0.0328   1.0000   0.6965
  -2.500  -0.2502   0.02273   0.01534  -0.0257   1.0000   0.7546
  -2.250  -0.2516   0.02272   0.01533  -0.0185   1.0000   0.8032
  -2.000  -0.2527   0.02251   0.01510  -0.0117   1.0000   0.8517
  -1.750  -0.2472   0.02219   0.01471  -0.0064   1.0000   0.9066
  -1.500  -0.1291   0.02268   0.01455  -0.0220   1.0000   1.0000
  -1.250  -0.1411   0.02212   0.01395  -0.0188   1.0000   1.0000
  -1.000  -0.1346   0.02187   0.01352  -0.0185   1.0000   1.0000
  -0.750  -0.1148   0.02197   0.01339  -0.0201   1.0000   1.0000
  -0.500  -0.0904   0.02227   0.01345  -0.0223   1.0000   1.0000
  -0.250  -0.0652   0.02271   0.01367  -0.0244   1.0000   1.0000
   0.000  -0.0404   0.02326   0.01398  -0.0263   1.0000   1.0000
   0.250  -0.0166   0.02388   0.01440  -0.0279   1.0000   1.0000
   0.500   0.0063   0.02456   0.01491  -0.0293   1.0000   1.0000
   0.750   0.0379   0.02555   0.01573  -0.0322   0.9957   1.0000
   1.000   0.0877   0.02694   0.01693  -0.0383   0.9819   1.0000
   1.250   0.1325   0.02811   0.01796  -0.0432   0.9678   1.0000
   1.500   0.1752   0.02916   0.01890  -0.0476   0.9536   1.0000
   1.750   0.2155   0.03013   0.01979  -0.0515   0.9398   1.0000
   2.000   0.2548   0.03106   0.02066  -0.0550   0.9259   1.0000
   2.250   0.2932   0.03194   0.02151  -0.0582   0.9120   1.0000
   2.500   0.3304   0.03280   0.02235  -0.0611   0.8980   1.0000
   2.750   0.3669   0.03363   0.02319  -0.0637   0.8839   1.0000
   3.000   0.4025   0.03444   0.02404  -0.0661   0.8698   1.0000
   3.250   0.4374   0.03524   0.02488  -0.0683   0.8555   1.0000
   3.500   0.4720   0.03601   0.02571  -0.0702   0.8408   1.0000
   3.750   0.5061   0.03676   0.02656  -0.0720   0.8260   1.0000
   4.000   0.5404   0.03746   0.02736  -0.0736   0.8107   1.0000
   4.250   0.5754   0.03808   0.02809  -0.0751   0.7948   1.0000
   4.500   0.6124   0.03856   0.02875  -0.0765   0.7786   1.0000
   4.750   0.6529   0.03880   0.02916  -0.0781   0.7623   1.0000
   5.000   0.6996   0.03860   0.02918  -0.0800   0.7457   1.0000
   5.250   0.7328   0.03877   0.02957  -0.0801   0.7267   1.0000
   5.500   0.7715   0.03850   0.02953  -0.0804   0.7070   1.0000
   5.750   0.8436   0.03620   0.02763  -0.0831   0.6874   1.0000
   6.000   0.8846   0.03529   0.02702  -0.0826   0.6631   1.0000
   6.250   0.9413   0.03316   0.02520  -0.0828   0.6356   1.0000
   6.500   0.9879   0.03148   0.02377  -0.0820   0.6025   1.0000
   6.750   1.0282   0.03005   0.02247  -0.0804   0.5636   1.0000
   7.000   1.0561   0.02923   0.02168  -0.0775   0.5182   1.0000
   7.250   1.0780   0.02868   0.02100  -0.0740   0.4652   1.0000
   7.500   1.0907   0.02881   0.02089  -0.0697   0.4061   1.0000
   7.750   1.0990   0.02968   0.02133  -0.0653   0.3456   1.0000
   8.000   1.1063   0.03119   0.02241  -0.0615   0.2898   1.0000
   8.250   1.1154   0.03328   0.02415  -0.0583   0.2406   1.0000
   8.500   1.1254   0.03567   0.02621  -0.0554   0.1973   1.0000
   8.750   1.1346   0.03809   0.02817  -0.0530   0.1601   1.0000
   9.000   1.1464   0.04083   0.03081  -0.0508   0.1313   1.0000
   9.250   1.1632   0.04389   0.03409  -0.0491   0.1123   1.0000
   9.500   1.1855   0.04762   0.03801  -0.0482   0.1013   1.0000
   9.750   1.2088   0.05127   0.04171  -0.0478   0.0934   1.0000
  10.000   1.2137   0.05493   0.04591  -0.0452   0.0899   1.0000
  10.250   1.2142   0.05850   0.04998  -0.0423   0.0873   1.0000
  10.500   1.2122   0.06224   0.05414  -0.0395   0.0856   1.0000
  10.750   1.2047   0.06618   0.05846  -0.0366   0.0850   1.0000
  11.000   1.1893   0.07004   0.06267  -0.0333   0.0853   1.0000
  11.250   1.1687   0.07408   0.06701  -0.0303   0.0857   1.0000
  11.500   1.1446   0.07848   0.07168  -0.0283   0.0865   1.0000
  11.750   1.1185   0.08344   0.07687  -0.0277   0.0874   1.0000
  12.000   1.0915   0.08912   0.08274  -0.0285   0.0885   1.0000
  12.250   1.0643   0.09566   0.08941  -0.0308   0.0897   1.0000
  12.500   1.0409   0.10285   0.09670  -0.0340   0.0909   1.0000
  12.750   1.0249   0.11013   0.10403  -0.0372   0.0919   1.0000
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