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EPPLER 715 AIRFOIL (e715-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 715 AIRFOIL (e715-il)
Reynolds number: 50,000
Max Cl/Cd: 5.65 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e715-il-50000.txt
Download as CSV file: xf-e715-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3705   0.11703   0.11126  -0.0105   1.0000   0.2876
 -10.000  -0.4272   0.09829   0.09271  -0.0295   1.0000   0.1544
  -9.750  -0.4243   0.09244   0.08693  -0.0327   1.0000   0.1488
  -9.500  -0.4971   0.07455   0.06929  -0.0508   1.0000   0.1222
  -9.250  -0.5818   0.06618   0.06081  -0.0596   1.0000   0.1094
  -9.000  -0.6072   0.06631   0.06108  -0.0547   1.0000   0.1089
  -8.750  -0.6337   0.06551   0.06029  -0.0508   1.0000   0.1084
  -8.500  -0.6339   0.05921   0.05351  -0.0564   0.9860   0.1084
  -8.250  -0.6258   0.05364   0.04728  -0.0607   0.9733   0.1092
  -8.000  -0.5992   0.04934   0.04289  -0.0636   0.9638   0.1141
  -7.750  -0.5763   0.04526   0.03820  -0.0667   0.9545   0.1209
  -7.500  -0.5563   0.04214   0.03476  -0.0677   0.9451   0.1285
  -7.250  -0.5248   0.03914   0.03138  -0.0702   0.9380   0.1422
  -7.000  -0.5027   0.03709   0.02916  -0.0704   0.9295   0.1575
  -6.750  -0.4673   0.03480   0.02671  -0.0726   0.9232   0.1846
  -6.500  -0.4515   0.03357   0.02553  -0.0713   0.9151   0.2104
  -6.250  -0.4226   0.03210   0.02430  -0.0720   0.9092   0.2563
  -6.000  -0.4110   0.03170   0.02427  -0.0695   0.9024   0.2980
  -5.750  -0.3878   0.03246   0.02544  -0.0676   0.8961   0.3553
  -5.500  -0.3640   0.03449   0.02766  -0.0646   0.8901   0.4035
  -5.250  -0.3495   0.03594   0.02907  -0.0612   0.8841   0.4406
  -5.000  -0.3205   0.03775   0.03088  -0.0587   0.8794   0.4772
  -4.750  -0.3095   0.03845   0.03147  -0.0553   0.8746   0.5056
  -4.500  -0.3042   0.03867   0.03155  -0.0519   0.8697   0.5325
  -4.250  -0.2850   0.03921   0.03203  -0.0491   0.8654   0.5587
  -4.000  -0.2632   0.03940   0.03211  -0.0472   0.8619   0.5860
  -3.750  -0.2699   0.03940   0.03204  -0.0424   0.8588   0.6033
  -3.500  -0.2675   0.03922   0.03174  -0.0393   0.8555   0.6246
  -3.250  -0.2577   0.03921   0.03164  -0.0363   0.8525   0.6442
  -3.000  -0.2448   0.03918   0.03151  -0.0340   0.8500   0.6646
  -2.750  -0.2281   0.03909   0.03127  -0.0329   0.8477   0.6861
  -2.500  -0.2199   0.03904   0.03110  -0.0306   0.8459   0.7038
  -2.250  -0.2148   0.03900   0.03097  -0.0279   0.8445   0.7198
  -2.000  -0.2070   0.03902   0.03090  -0.0257   0.8437   0.7360
  -1.750  -0.1971   0.03907   0.03086  -0.0239   0.8434   0.7521
  -1.500  -0.1859   0.03914   0.03084  -0.0224   0.8429   0.7678
  -1.250  -0.1744   0.03925   0.03087  -0.0211   0.8428   0.7832
  -1.000  -0.1614   0.03946   0.03097  -0.0201   0.8439   0.7985
  -0.750  -0.1467   0.03973   0.03115  -0.0195   0.8451   0.8140
  -0.500  -0.1298   0.04009   0.03145  -0.0192   0.8464   0.8298
  -0.250  -0.1348   0.04007   0.03141  -0.0164   0.8555   0.8441
   0.000  -0.1160   0.04062   0.03194  -0.0168   0.8607   0.8619
   0.250  -0.1283   0.04048   0.03187  -0.0136   0.8876   0.8785
   0.500  -0.2406   0.03598   0.02765   0.0071   1.0000   0.8867
   0.750  -0.2048   0.03672   0.02843   0.0030   1.0000   0.9180
   1.000  -0.1648   0.03732   0.02901  -0.0030   1.0000   0.9658
   1.250  -0.1412   0.03789   0.02941  -0.0060   1.0000   1.0000
   1.500  -0.1183   0.03866   0.03000  -0.0087   1.0000   1.0000
   1.750  -0.0946   0.03961   0.03076  -0.0113   1.0000   1.0000
   2.000  -0.0711   0.04068   0.03164  -0.0138   1.0000   1.0000
   2.250  -0.0482   0.04183   0.03262  -0.0160   1.0000   1.0000
   2.500  -0.0262   0.04304   0.03367  -0.0179   1.0000   1.0000
   2.750  -0.0050   0.04430   0.03477  -0.0196   1.0000   1.0000
   3.000   0.0380   0.04711   0.03740  -0.0256   0.9877   1.0000
   3.250   0.0834   0.05020   0.04034  -0.0317   0.9710   1.0000
   3.500   0.1264   0.05339   0.04339  -0.0371   0.9544   1.0000
   3.750   0.1557   0.05504   0.04497  -0.0398   0.9313   1.0000
   4.000   0.1898   0.05746   0.04731  -0.0432   0.9124   1.0000
   4.500   0.2555   0.06271   0.05242  -0.0490   0.8781   1.0000
   4.750   0.2751   0.06427   0.05396  -0.0496   0.8599   1.0000
   5.000   0.2959   0.06596   0.05562  -0.0503   0.8408   1.0000
   5.250   0.3191   0.06802   0.05766  -0.0514   0.8237   1.0000
   5.500   0.3423   0.07017   0.05980  -0.0525   0.8068   1.0000
   5.750   0.3643   0.07233   0.06197  -0.0534   0.7907   1.0000
   6.000   0.3852   0.07451   0.06416  -0.0541   0.7749   1.0000
   6.250   0.4059   0.07673   0.06641  -0.0548   0.7589   1.0000
   6.500   0.4247   0.07893   0.06864  -0.0553   0.7435   1.0000
   6.750   0.4428   0.08115   0.07090  -0.0557   0.7282   1.0000
   7.000   0.4596   0.08340   0.07318  -0.0560   0.7131   1.0000
   7.250   0.4762   0.08569   0.07552  -0.0563   0.6980   1.0000
   7.500   0.4918   0.08802   0.07790  -0.0565   0.6831   1.0000
   7.750   0.5069   0.09040   0.08035  -0.0567   0.6682   1.0000
   8.000   0.5215   0.09285   0.08286  -0.0569   0.6538   1.0000
   8.250   0.5361   0.09540   0.08548  -0.0571   0.6397   1.0000
   8.500   0.5512   0.09804   0.08819  -0.0574   0.6254   1.0000
   8.750   0.5688   0.10097   0.09122  -0.0580   0.6119   1.0000
   9.000   0.5862   0.10387   0.09420  -0.0584   0.5973   1.0000
   9.250   0.6044   0.10688   0.09730  -0.0589   0.5826   1.0000
   9.500   0.6205   0.10973   0.10025  -0.0591   0.5675   1.0000
   9.750   0.6360   0.11259   0.10322  -0.0593   0.5523   1.0000
  10.000   0.6489   0.11532   0.10605  -0.0594   0.5369   1.0000
  10.250   0.6612   0.11804   0.10886  -0.0595   0.5217   1.0000
  10.500   0.6486   0.11983   0.11069  -0.0591   0.5108   1.0000
  10.750   0.6562   0.12271   0.11365  -0.0593   0.4973   1.0000
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