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NACA 16-015 (naca16015-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 16-015 (naca16015-il)
Reynolds number: 200,000
Max Cl/Cd: 40.35 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca16015-il-200000.txt
Download as CSV file: xf-naca16015-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 16-015                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.8181   0.06316   0.05905  -0.0468   1.0000   0.0469
 -11.250  -0.9164   0.06823   0.06371  -0.0361   1.0000   0.0439
 -11.000  -0.9393   0.06563   0.06102  -0.0300   1.0000   0.0432
 -10.750  -1.0441   0.05940   0.05395  -0.0091   1.0000   0.0371
 -10.500  -1.0593   0.05765   0.05196  -0.0023   1.0000   0.0369
 -10.250  -1.0731   0.05489   0.04895   0.0039   1.0000   0.0369
 -10.000  -1.0846   0.05152   0.04530   0.0097   1.0000   0.0371
  -9.750  -1.0888   0.04837   0.04195   0.0143   1.0000   0.0377
  -9.500  -1.0805   0.04693   0.04054   0.0167   1.0000   0.0388
  -9.250  -1.0803   0.04464   0.03800   0.0212   1.0000   0.0392
  -9.000  -1.0782   0.04210   0.03513   0.0256   1.0000   0.0394
  -8.750  -1.0717   0.03994   0.03269   0.0292   1.0000   0.0400
  -8.500  -1.0620   0.03802   0.03050   0.0324   1.0000   0.0408
  -8.250  -1.0509   0.03655   0.02879   0.0353   1.0000   0.0423
  -8.000  -1.0386   0.03520   0.02713   0.0381   1.0000   0.0439
  -7.750  -1.0254   0.03410   0.02572   0.0409   1.0000   0.0450
  -7.500  -0.9988   0.03144   0.02282   0.0408   1.0000   0.0466
  -7.250  -0.9778   0.03024   0.02163   0.0415   1.0000   0.0488
  -7.000  -0.9599   0.02947   0.02078   0.0431   1.0000   0.0513
  -6.750  -0.9396   0.02861   0.01978   0.0443   1.0000   0.0536
  -6.500  -0.9198   0.02791   0.01892   0.0457   1.0000   0.0553
  -6.250  -0.8938   0.02644   0.01748   0.0455   1.0000   0.0587
  -6.000  -0.8765   0.02581   0.01685   0.0471   1.0000   0.0617
  -5.750  -0.8591   0.02520   0.01619   0.0489   1.0000   0.0645
  -5.500  -0.8401   0.02481   0.01568   0.0503   0.9996   0.0674
  -5.250  -0.8117   0.02387   0.01484   0.0495   0.9969   0.0730
  -5.000  -0.7830   0.02355   0.01447   0.0488   0.9945   0.0787
  -4.750  -0.7593   0.02288   0.01385   0.0491   0.9906   0.0870
  -4.500  -0.7360   0.02235   0.01339   0.0495   0.9872   0.1008
  -4.250  -0.7150   0.02157   0.01294   0.0503   0.9845   0.1486
  -4.000  -0.7130   0.01992   0.01227   0.0546   0.9804   0.3113
  -3.750  -0.7237   0.01793   0.01163   0.0621   0.9758   0.5533
  -3.500  -0.6830   0.01832   0.01325   0.0611   0.9749   0.8126
  -3.250  -0.6370   0.01961   0.01447   0.0582   0.9732   0.8492
  -3.000  -0.6047   0.02068   0.01542   0.0579   0.9709   0.8712
  -2.750  -0.5515   0.02237   0.01699   0.0536   0.9690   0.8844
  -2.500  -0.4383   0.02568   0.02013   0.0377   0.9726   0.8926
  -2.250  -0.3481   0.02823   0.02257   0.0266   0.9743   0.9064
  -2.000  -0.2936   0.02925   0.02349   0.0212   0.9734   0.9173
  -1.750  -0.2432   0.02960   0.02377   0.0159   0.9722   0.9205
  -1.500  -0.2251   0.02969   0.02380   0.0172   0.9677   0.9292
  -1.250  -0.1831   0.02975   0.02382   0.0135   0.9650   0.9317
  -1.000  -0.1404   0.02984   0.02387   0.0096   0.9626   0.9344
  -0.750  -0.1007   0.02994   0.02393   0.0062   0.9603   0.9382
  -0.500  -0.0700   0.03010   0.02407   0.0047   0.9581   0.9444
  -0.250  -0.0377   0.02998   0.02394   0.0030   0.9531   0.9468
   0.000   0.0000   0.02996   0.02392   0.0000   0.9496   0.9496
   0.250   0.0376   0.02998   0.02394  -0.0029   0.9468   0.9531
   0.500   0.0699   0.03010   0.02406  -0.0047   0.9444   0.9581
   0.750   0.1007   0.02993   0.02393  -0.0062   0.9382   0.9603
   1.000   0.1403   0.02983   0.02386  -0.0096   0.9344   0.9626
   1.250   0.1831   0.02974   0.02381  -0.0135   0.9317   0.9650
   1.500   0.2246   0.02968   0.02380  -0.0171   0.9291   0.9678
   1.750   0.2431   0.02959   0.02376  -0.0159   0.9205   0.9722
   2.000   0.2934   0.02924   0.02348  -0.0212   0.9174   0.9735
   2.250   0.3481   0.02822   0.02256  -0.0266   0.9064   0.9743
   2.500   0.4383   0.02567   0.02011  -0.0377   0.8926   0.9726
   2.750   0.5522   0.02233   0.01696  -0.0537   0.8845   0.9689
   3.000   0.6055   0.02064   0.01539  -0.0580   0.8713   0.9708
   3.250   0.6370   0.01960   0.01445  -0.0582   0.8491   0.9732
   3.750   0.7235   0.01793   0.01162  -0.0620   0.5532   0.9759
   4.000   0.7129   0.01991   0.01226  -0.0546   0.3119   0.9805
   4.250   0.7149   0.02156   0.01292  -0.0503   0.1489   0.9845
   4.500   0.7360   0.02234   0.01338  -0.0495   0.1008   0.9872
   4.750   0.7593   0.02287   0.01384  -0.0491   0.0870   0.9906
   5.000   0.7829   0.02354   0.01446  -0.0488   0.0787   0.9944
   5.250   0.8116   0.02386   0.01483  -0.0495   0.0730   0.9969
   5.500   0.8397   0.02480   0.01567  -0.0502   0.0674   0.9996
   5.750   0.8590   0.02519   0.01618  -0.0489   0.0645   1.0000
   6.000   0.8764   0.02580   0.01685  -0.0471   0.0617   1.0000
   6.250   0.8938   0.02643   0.01748  -0.0455   0.0587   1.0000
   6.500   0.9198   0.02790   0.01891  -0.0457   0.0553   1.0000
   6.750   0.9396   0.02861   0.01978  -0.0443   0.0536   1.0000
   7.000   0.9597   0.02945   0.02076  -0.0430   0.0513   1.0000
   7.250   0.9777   0.03022   0.02161  -0.0415   0.0488   1.0000
   7.500   0.9986   0.03142   0.02281  -0.0408   0.0466   1.0000
   7.750   1.0253   0.03409   0.02571  -0.0409   0.0450   1.0000
   8.000   1.0384   0.03517   0.02711  -0.0381   0.0439   1.0000
   8.250   1.0507   0.03650   0.02873  -0.0353   0.0423   1.0000
   8.500   1.0619   0.03799   0.03046  -0.0324   0.0408   1.0000
   8.750   1.0715   0.03994   0.03269  -0.0292   0.0400   1.0000
   9.000   1.0780   0.04211   0.03515  -0.0256   0.0395   1.0000
   9.250   1.0800   0.04469   0.03805  -0.0211   0.0392   1.0000
   9.500   1.0789   0.04713   0.04078  -0.0164   0.0389   1.0000
   9.750   1.0893   0.04834   0.04190  -0.0144   0.0376   1.0000
  10.000   1.0845   0.05153   0.04531  -0.0097   0.0371   1.0000
  10.250   1.0731   0.05487   0.04892  -0.0039   0.0369   1.0000
  10.500   1.0596   0.05757   0.05188   0.0023   0.0369   1.0000
  10.750   1.0442   0.05929   0.05385   0.0091   0.0371   1.0000
  11.000   0.8605   0.05595   0.05158   0.0371   0.0430   1.0000
  11.250   0.8328   0.05905   0.05481   0.0428   0.0435   1.0000
  11.500   0.8048   0.06246   0.05834   0.0478   0.0439   1.0000
  11.750   0.7793   0.06629   0.06226   0.0517   0.0444   1.0000
  12.000   0.6776   0.09731   0.09379   0.0508   0.0724   1.0000
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