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E231 (e231-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E231 (e231-il)
Reynolds number: 50,000
Max Cl/Cd: 30.46 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e231-il-50000-n5.txt
Download as CSV file: xf-e231-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E231                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.2879   0.11580   0.10940  -0.0464   1.0000   0.0488
 -11.000  -0.3684   0.11696   0.10994  -0.0465   1.0000   0.0488
 -10.750  -0.3680   0.11325   0.10630  -0.0475   1.0000   0.0462
 -10.250  -0.3833   0.10411   0.09736  -0.0523   1.0000   0.0401
 -10.000  -0.3847   0.10112   0.09444  -0.0518   1.0000   0.0393
  -9.750  -0.3902   0.09820   0.09162  -0.0514   1.0000   0.0387
  -9.500  -0.4005   0.09507   0.08860  -0.0509   1.0000   0.0381
  -9.250  -0.4128   0.09237   0.08600  -0.0501   1.0000   0.0376
  -9.000  -0.4296   0.08940   0.08313  -0.0494   1.0000   0.0372
  -8.750  -0.4485   0.08661   0.08042  -0.0486   1.0000   0.0367
  -8.500  -0.4704   0.08423   0.07811  -0.0468   1.0000   0.0362
  -8.250  -0.4954   0.08219   0.07613  -0.0438   1.0000   0.0359
  -8.000  -0.5195   0.08035   0.07432  -0.0401   1.0000   0.0355
  -7.750  -0.5398   0.07784   0.07179  -0.0371   1.0000   0.0351
  -7.500  -0.5581   0.07503   0.06894  -0.0342   1.0000   0.0347
  -7.250  -0.5587   0.07003   0.06371  -0.0356   0.9937   0.0339
  -7.000  -0.5584   0.06535   0.05873  -0.0361   0.9874   0.0331
  -6.750  -0.5542   0.06076   0.05374  -0.0361   0.9820   0.0323
  -6.500  -0.5493   0.05669   0.04923  -0.0351   0.9762   0.0318
  -6.250  -0.5375   0.05282   0.04478  -0.0345   0.9714   0.0312
  -6.000  -0.5261   0.04967   0.04123  -0.0332   0.9666   0.0313
  -5.750  -0.5111   0.04668   0.03780  -0.0321   0.9619   0.0315
  -5.500  -0.4907   0.04426   0.03509  -0.0321   0.9581   0.0331
  -5.250  -0.4719   0.04222   0.03264  -0.0312   0.9539   0.0346
  -5.000  -0.4516   0.04007   0.03005  -0.0301   0.9495   0.0367
  -4.750  -0.4252   0.03804   0.02752  -0.0299   0.9458   0.0386
  -4.500  -0.3936   0.03610   0.02507  -0.0301   0.9430   0.0404
  -4.250  -0.3703   0.03432   0.02317  -0.0293   0.9392   0.0433
  -4.000  -0.3438   0.03318   0.02185  -0.0290   0.9351   0.0497
  -3.750  -0.3129   0.03194   0.02042  -0.0293   0.9320   0.0566
  -3.500  -0.2804   0.03084   0.01920  -0.0302   0.9292   0.0727
  -3.250  -0.2593   0.02984   0.01819  -0.0291   0.9244   0.0955
  -3.000  -0.2384   0.02819   0.01720  -0.0284   0.9201   0.1830
  -2.750  -0.1858   0.02669   0.01872  -0.0285   0.9217   0.8624
  -2.500  -0.0031   0.02806   0.01885  -0.0552   0.9328   0.9860
  -2.250   0.0562   0.02790   0.01822  -0.0624   0.9312   1.0000
  -2.000   0.0765   0.02796   0.01803  -0.0622   0.9250   1.0000
  -1.750   0.0972   0.02804   0.01790  -0.0618   0.9186   1.0000
  -1.500   0.1252   0.02815   0.01777  -0.0628   0.9137   1.0000
  -1.250   0.1385   0.02831   0.01778  -0.0610   0.9059   1.0000
  -1.000   0.1689   0.02846   0.01774  -0.0623   0.9011   1.0000
  -0.750   0.1797   0.02868   0.01784  -0.0600   0.8928   1.0000
  -0.500   0.2093   0.02886   0.01788  -0.0610   0.8875   1.0000
  -0.250   0.2207   0.02912   0.01802  -0.0587   0.8790   1.0000
   0.000   0.2506   0.02931   0.01810  -0.0597   0.8735   1.0000
   0.250   0.2616   0.02959   0.01832  -0.0572   0.8645   1.0000
   0.500   0.2937   0.02978   0.01841  -0.0585   0.8590   1.0000
   0.750   0.3029   0.03009   0.01867  -0.0556   0.8492   1.0000
   1.000   0.3386   0.03024   0.01877  -0.0574   0.8441   1.0000
   1.250   0.3461   0.03057   0.01907  -0.0542   0.8334   1.0000
   1.500   0.3645   0.03083   0.01930  -0.0529   0.8247   1.0000
   1.750   0.3921   0.03099   0.01946  -0.0531   0.8173   1.0000
   2.000   0.4036   0.03129   0.01975  -0.0505   0.8068   1.0000
   2.250   0.4427   0.03130   0.01977  -0.0525   0.8011   1.0000
   2.500   0.4507   0.03160   0.02008  -0.0493   0.7893   1.0000
   2.750   0.4634   0.03184   0.02036  -0.0468   0.7780   1.0000
   3.000   0.4844   0.03196   0.02051  -0.0456   0.7682   1.0000
   3.250   0.5155   0.03188   0.02050  -0.0459   0.7599   1.0000
   3.500   0.5274   0.03207   0.02072  -0.0432   0.7475   1.0000
   3.750   0.5419   0.03219   0.02090  -0.0408   0.7353   1.0000
   4.000   0.5591   0.03224   0.02105  -0.0388   0.7234   1.0000
   4.250   0.5798   0.03218   0.02107  -0.0373   0.7118   1.0000
   4.500   0.6155   0.03167   0.02069  -0.0377   0.7030   1.0000
   4.750   0.6313   0.03160   0.02070  -0.0353   0.6896   1.0000
   5.000   0.6486   0.03145   0.02068  -0.0330   0.6760   1.0000
   5.250   0.6673   0.03121   0.02056  -0.0308   0.6622   1.0000
   5.500   0.6876   0.03090   0.02037  -0.0288   0.6479   1.0000
   5.750   0.7099   0.03049   0.02009  -0.0270   0.6332   1.0000
   6.000   0.7227   0.03042   0.02017  -0.0241   0.6154   1.0000
   6.250   0.7403   0.03020   0.02007  -0.0217   0.5972   1.0000
   6.500   0.7656   0.02965   0.01966  -0.0201   0.5787   1.0000
   6.750   0.7859   0.02937   0.01951  -0.0180   0.5572   1.0000
   7.000   0.8149   0.02877   0.01904  -0.0169   0.5338   1.0000
   7.250   0.8363   0.02859   0.01891  -0.0150   0.5064   1.0000
   7.500   0.8583   0.02848   0.01880  -0.0132   0.4763   1.0000
   7.750   0.8747   0.02872   0.01901  -0.0109   0.4452   1.0000
   8.000   0.8885   0.02917   0.01944  -0.0084   0.4140   1.0000
   8.250   0.9001   0.02980   0.02000  -0.0058   0.3840   1.0000
   8.500   0.9097   0.03060   0.02072  -0.0032   0.3552   1.0000
   8.750   0.9184   0.03152   0.02158  -0.0007   0.3280   1.0000
   9.000   0.9267   0.03254   0.02253   0.0017   0.3028   1.0000
   9.250   0.9344   0.03365   0.02361   0.0040   0.2789   1.0000
   9.500   0.9422   0.03487   0.02483   0.0061   0.2562   1.0000
   9.750   0.9494   0.03614   0.02604   0.0082   0.2355   1.0000
  10.000   0.9571   0.03750   0.02750   0.0100   0.2154   1.0000
  10.250   0.9646   0.03893   0.02894   0.0118   0.1972   1.0000
  10.500   0.9725   0.04043   0.03044   0.0135   0.1808   1.0000
  10.750   0.9801   0.04199   0.03201   0.0151   0.1656   1.0000
  11.000   0.9871   0.04365   0.03371   0.0166   0.1513   1.0000
  11.250   0.9949   0.04538   0.03551   0.0179   0.1384   1.0000
  11.500   1.0006   0.04725   0.03750   0.0193   0.1262   1.0000
  11.750   1.0082   0.04920   0.03962   0.0205   0.1153   1.0000
  12.000   1.0145   0.05131   0.04188   0.0217   0.1055   1.0000
  12.250   1.0182   0.05344   0.04406   0.0228   0.0971   1.0000
  12.500   1.0216   0.05591   0.04679   0.0238   0.0891   1.0000
  12.750   1.0237   0.05852   0.04954   0.0248   0.0822   1.0000
  13.000   1.0224   0.06128   0.05247   0.0255   0.0760   1.0000
  13.250   1.0237   0.06425   0.05558   0.0261   0.0709   1.0000
  13.500   1.0187   0.06789   0.05954   0.0265   0.0666   1.0000
  13.750   1.0164   0.07079   0.06244   0.0266   0.0623   1.0000
  14.000   1.0082   0.07501   0.06690   0.0264   0.0594   1.0000
  14.250   0.9944   0.08013   0.07236   0.0255   0.0574   1.0000
  14.500   0.9799   0.08564   0.07815   0.0240   0.0561   1.0000
  14.750   0.9627   0.09174   0.08446   0.0218   0.0548   1.0000
  15.000   0.9417   0.09910   0.09205   0.0185   0.0549   1.0000
  15.250   0.9145   0.10840   0.10156   0.0136   0.0558   1.0000
  15.500   0.8819   0.11999   0.11328   0.0070   0.0574   1.0000
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