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EPPLER 715 AIRFOIL (e715-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 715 AIRFOIL (e715-il)
Reynolds number: 50,000
Max Cl/Cd: 15.73 at α=12.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e715-il-50000-n5.txt
Download as CSV file: xf-e715-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 715 AIRFOIL                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.4870   0.10500   0.09875  -0.0244   1.0000   0.0469
 -11.500  -0.4983   0.09709   0.09089  -0.0290   1.0000   0.0467
 -11.250  -0.5156   0.08847   0.08233  -0.0344   1.0000   0.0463
 -11.000  -0.5373   0.07990   0.07373  -0.0405   1.0000   0.0458
 -10.750  -0.5598   0.07221   0.06598  -0.0464   1.0000   0.0453
 -10.500  -0.5800   0.06569   0.05936  -0.0517   1.0000   0.0448
 -10.250  -0.5987   0.06005   0.05359  -0.0563   1.0000   0.0448
 -10.000  -0.6124   0.05579   0.04918  -0.0590   1.0000   0.0450
  -9.750  -0.6210   0.05218   0.04536  -0.0604   1.0000   0.0459
  -9.500  -0.6129   0.04781   0.04031  -0.0642   0.9134   0.0478
  -9.250  -0.5933   0.04550   0.03794  -0.0656   0.8833   0.0511
  -9.000  -0.5793   0.04312   0.03519  -0.0657   0.8619   0.0541
  -8.750  -0.5662   0.04075   0.03223  -0.0650   0.8448   0.0581
  -8.500  -0.5503   0.03920   0.03069  -0.0643   0.8307   0.0629
  -8.250  -0.5331   0.03748   0.02860  -0.0634   0.8182   0.0688
  -8.000  -0.5165   0.03601   0.02711  -0.0626   0.8071   0.0759
  -7.750  -0.4993   0.03456   0.02545  -0.0616   0.7977   0.0848
  -7.500  -0.4820   0.03324   0.02397  -0.0608   0.7887   0.0962
  -7.250  -0.4655   0.03196   0.02263  -0.0600   0.7804   0.1101
  -7.000  -0.4495   0.03069   0.02140  -0.0592   0.7727   0.1273
  -6.750  -0.4325   0.02947   0.02018  -0.0586   0.7655   0.1509
  -6.500  -0.4153   0.02830   0.01909  -0.0580   0.7587   0.1808
  -6.250  -0.3978   0.02726   0.01822  -0.0573   0.7529   0.2187
  -6.000  -0.3784   0.02651   0.01765  -0.0567   0.7463   0.2649
  -5.750  -0.3579   0.02622   0.01753  -0.0556   0.7409   0.3132
  -5.500  -0.3353   0.02641   0.01779  -0.0544   0.7352   0.3572
  -5.250  -0.3116   0.02674   0.01802  -0.0535   0.7295   0.3950
  -5.000  -0.2876   0.02716   0.01822  -0.0523   0.7249   0.4253
  -4.750  -0.2630   0.02761   0.01852  -0.0514   0.7198   0.4498
  -4.500  -0.2388   0.02788   0.01859  -0.0508   0.7148   0.4726
  -4.250  -0.2143   0.02810   0.01862  -0.0498   0.7105   0.4917
  -4.000  -0.1899   0.02822   0.01854  -0.0490   0.7063   0.5094
  -3.750  -0.1655   0.02831   0.01850  -0.0486   0.7012   0.5256
  -3.500  -0.1406   0.02834   0.01837  -0.0480   0.6970   0.5407
  -3.250  -0.1156   0.02831   0.01816  -0.0474   0.6936   0.5548
  -3.000  -0.0909   0.02835   0.01807  -0.0472   0.6893   0.5680
  -2.750  -0.0662   0.02838   0.01797  -0.0471   0.6846   0.5808
  -2.500  -0.0411   0.02837   0.01780  -0.0468   0.6808   0.5928
  -2.250  -0.0154   0.02833   0.01765  -0.0463   0.6777   0.6029
  -2.000   0.0092   0.02846   0.01768  -0.0464   0.6735   0.6134
  -1.750   0.0335   0.02858   0.01770  -0.0464   0.6691   0.6240
  -1.500   0.0585   0.02864   0.01768  -0.0461   0.6654   0.6330
  -1.250   0.0844   0.02867   0.01757  -0.0459   0.6624   0.6428
  -1.000   0.1085   0.02893   0.01778  -0.0460   0.6584   0.6515
  -0.750   0.1324   0.02921   0.01802  -0.0461   0.6540   0.6601
  -0.500   0.1576   0.02939   0.01812  -0.0461   0.6503   0.6691
  -0.250   0.1840   0.02950   0.01816  -0.0460   0.6473   0.6773
   0.000   0.2079   0.02988   0.01848  -0.0462   0.6435   0.6863
   0.250   0.2298   0.03037   0.01901  -0.0463   0.6387   0.6943
   0.500   0.2546   0.03070   0.01930  -0.0464   0.6350   0.7037
   0.750   0.2808   0.03087   0.01946  -0.0462   0.6320   0.7126
   1.000   0.3040   0.03134   0.01995  -0.0463   0.6282   0.7222
   1.250   0.3231   0.03210   0.02078  -0.0463   0.6228   0.7327
   1.500   0.3468   0.03249   0.02122  -0.0462   0.6190   0.7437
   1.750   0.3733   0.03271   0.02148  -0.0460   0.6161   0.7564
   2.000   0.3919   0.03351   0.02240  -0.0459   0.6111   0.7712
   2.250   0.4110   0.03429   0.02331  -0.0458   0.6058   0.7892
   2.500   0.4377   0.03462   0.02379  -0.0459   0.6021   0.8142
   2.750   0.4746   0.03474   0.02407  -0.0473   0.5995   0.8546
   3.000   0.5078   0.03627   0.02581  -0.0518   0.5918   1.0000
   3.250   0.5308   0.03700   0.02647  -0.0521   0.5873   1.0000
   3.500   0.5588   0.03743   0.02681  -0.0523   0.5843   1.0000
   3.750   0.5635   0.03938   0.02876  -0.0519   0.5758   1.0000
   4.000   0.5869   0.04009   0.02942  -0.0518   0.5714   1.0000
   4.250   0.6163   0.04037   0.02969  -0.0518   0.5684   1.0000
   4.500   0.6147   0.04270   0.03204  -0.0510   0.5583   1.0000
   4.750   0.6420   0.04310   0.03243  -0.0507   0.5545   1.0000
   5.250   0.6671   0.04582   0.03521  -0.0495   0.5402   1.0000
   5.500   0.6952   0.04612   0.03553  -0.0491   0.5363   1.0000
   5.750   0.6919   0.04847   0.03791  -0.0480   0.5254   1.0000
   6.000   0.7256   0.04835   0.03787  -0.0477   0.5222   1.0000
   6.250   0.7154   0.05099   0.04053  -0.0462   0.5102   1.0000
   6.500   0.7411   0.05137   0.04098  -0.0456   0.5052   1.0000
   6.750   0.7422   0.05328   0.04293  -0.0445   0.4947   1.0000
   7.250   0.7718   0.05533   0.04513  -0.0428   0.4788   1.0000
   7.500   0.7732   0.05732   0.04718  -0.0419   0.4677   1.0000
   7.750   0.8051   0.05697   0.04695  -0.0412   0.4628   1.0000
   8.250   0.8113   0.06071   0.05082  -0.0395   0.4399   1.0000
   8.500   0.8409   0.06031   0.05058  -0.0386   0.4339   1.0000
   8.750   0.8433   0.06225   0.05260  -0.0378   0.4216   1.0000
   9.000   0.8504   0.06381   0.05426  -0.0371   0.4101   1.0000
   9.250   0.8833   0.06274   0.05338  -0.0359   0.4042   1.0000
   9.500   0.8868   0.06461   0.05535  -0.0353   0.3914   1.0000
   9.750   0.8932   0.06624   0.05708  -0.0346   0.3789   1.0000
  10.000   0.9044   0.06731   0.05828  -0.0338   0.3673   1.0000
  10.250   0.9383   0.06552   0.05668  -0.0322   0.3606   1.0000
  10.500   0.9458   0.06688   0.05818  -0.0315   0.3474   1.0000
  10.750   0.9554   0.06801   0.05944  -0.0307   0.3346   1.0000
  11.000   0.9689   0.06859   0.06015  -0.0298   0.3222   1.0000
  11.250   0.9887   0.06827   0.05998  -0.0285   0.3104   1.0000
  11.500   1.0146   0.06703   0.05889  -0.0269   0.2984   1.0000
  11.750   1.0349   0.06656   0.05855  -0.0255   0.2839   1.0000
  12.000   1.0498   0.06688   0.05894  -0.0244   0.2679   1.0000
  12.250   1.0624   0.06756   0.05965  -0.0234   0.2511   1.0000
  12.500   1.0737   0.06843   0.06051  -0.0224   0.2339   1.0000
  12.750   1.0828   0.06966   0.06169  -0.0216   0.2171   1.0000
  13.000   1.0885   0.07142   0.06338  -0.0210   0.2011   1.0000
  13.250   1.0916   0.07370   0.06565  -0.0207   0.1863   1.0000
  13.500   1.0923   0.07646   0.06838  -0.0207   0.1724   1.0000
  13.750   1.0920   0.07952   0.07145  -0.0210   0.1597   1.0000
  14.000   1.0915   0.08271   0.07467  -0.0213   0.1481   1.0000
  14.250   1.0917   0.08584   0.07780  -0.0217   0.1374   1.0000
  14.500   1.0947   0.08852   0.08040  -0.0218   0.1277   1.0000
  14.750   1.0918   0.09244   0.08444  -0.0227   0.1188   1.0000
  15.000   1.0905   0.09614   0.08820  -0.0235   0.1108   1.0000
  15.250   1.0934   0.09901   0.09103  -0.0240   0.1033   1.0000
  15.500   1.0877   0.10383   0.09606  -0.0255   0.0973   1.0000
  15.750   1.0899   0.10695   0.09919  -0.0263   0.0909   1.0000
  16.000   1.0841   0.11195   0.10437  -0.0280   0.0863   1.0000
  16.250   1.0762   0.11751   0.11012  -0.0303   0.0820   1.0000
  16.500   1.0849   0.11935   0.11183  -0.0305   0.0767   1.0000
  16.750   1.0665   0.12752   0.12034  -0.0345   0.0746   1.0000
  17.000   1.0439   0.13704   0.13012  -0.0396   0.0730   1.0000
  17.250   1.0081   0.15080   0.14404  -0.0474   0.0725   1.0000
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