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NACA 16009 (naca16009-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 16009 (naca16009-il)
Reynolds number: 200,000
Max Cl/Cd: 34.56 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca16009-il-200000-n5.txt
Download as CSV file: xf-naca16009-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 16009                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.6150   0.08858   0.08503  -0.0300   1.0000   0.0088
  -9.750  -0.6247   0.08219   0.07866  -0.0349   1.0000   0.0087
  -9.500  -0.6388   0.07674   0.07320  -0.0377   1.0000   0.0086
  -9.250  -0.6560   0.07255   0.06896  -0.0375   1.0000   0.0085
  -9.000  -0.6756   0.06933   0.06570  -0.0347   1.0000   0.0084
  -8.750  -0.6945   0.06643   0.06274  -0.0306   1.0000   0.0084
  -8.500  -0.7090   0.06310   0.05932  -0.0269   1.0000   0.0083
  -8.250  -0.7214   0.05968   0.05577  -0.0228   1.0000   0.0083
  -8.000  -0.7316   0.05618   0.05212  -0.0186   1.0000   0.0083
  -7.750  -0.7394   0.05259   0.04834  -0.0142   1.0000   0.0083
  -7.500  -0.7450   0.04891   0.04442  -0.0097   1.0000   0.0083
  -7.250  -0.7476   0.04519   0.04043  -0.0051   1.0000   0.0085
  -7.000  -0.7429   0.04199   0.03688  -0.0010   1.0000   0.0092
  -6.750  -0.7451   0.03806   0.03252   0.0038   1.0000   0.0098
  -6.500  -0.7429   0.03505   0.02920   0.0076   1.0000   0.0104
  -6.250  -0.7344   0.03220   0.02596   0.0111   1.0000   0.0105
  -6.000  -0.7221   0.02929   0.02260   0.0142   0.9999   0.0104
  -5.750  -0.6986   0.02644   0.01921   0.0151   0.9984   0.0105
  -5.500  -0.6733   0.02412   0.01648   0.0157   0.9970   0.0107
  -5.250  -0.6469   0.02223   0.01429   0.0160   0.9959   0.0110
  -5.000  -0.6195   0.02069   0.01253   0.0160   0.9947   0.0116
  -4.750  -0.5926   0.01941   0.01108   0.0161   0.9935   0.0126
  -4.500  -0.5669   0.01831   0.00984   0.0165   0.9918   0.0139
  -4.250  -0.5397   0.01777   0.00919   0.0163   0.9898   0.0167
  -4.000  -0.5153   0.01656   0.00789   0.0168   0.9877   0.0194
  -3.750  -0.4880   0.01587   0.00704   0.0167   0.9857   0.0238
  -3.500  -0.4601   0.01525   0.00638   0.0164   0.9840   0.0349
  -3.250  -0.4314   0.01468   0.00591   0.0158   0.9824   0.0660
  -3.000  -0.4090   0.01392   0.00552   0.0163   0.9795   0.1457
  -2.750  -0.3914   0.01260   0.00512   0.0175   0.9765   0.3544
  -2.500  -0.3795   0.01099   0.00487   0.0204   0.9737   0.6552
  -2.250  -0.3468   0.01100   0.00549   0.0207   0.9741   0.8467
  -2.000  -0.3113   0.01133   0.00577   0.0196   0.9732   0.8854
  -1.750  -0.2715   0.01205   0.00643   0.0181   0.9736   0.9239
  -1.500  -0.2151   0.01293   0.00717   0.0129   0.9772   0.9464
  -1.250  -0.1771   0.01302   0.00716   0.0104   0.9759   0.9510
  -1.000  -0.1453   0.01305   0.00711   0.0092   0.9734   0.9561
  -0.750  -0.1063   0.01307   0.00708   0.0063   0.9721   0.9579
  -0.500  -0.0681   0.01309   0.00705   0.0036   0.9707   0.9599
  -0.250  -0.0304   0.01310   0.00704   0.0010   0.9694   0.9622
   0.000   0.0000   0.01310   0.00703   0.0000   0.9658   0.9658
   0.250   0.0304   0.01310   0.00703  -0.0010   0.9622   0.9694
   0.500   0.0681   0.01309   0.00705  -0.0036   0.9599   0.9707
   0.750   0.1063   0.01307   0.00708  -0.0063   0.9579   0.9721
   1.000   0.1453   0.01304   0.00711  -0.0091   0.9561   0.9734
   1.250   0.1771   0.01302   0.00716  -0.0104   0.9511   0.9759
   1.500   0.2152   0.01293   0.00716  -0.0129   0.9464   0.9773
   1.750   0.2716   0.01205   0.00643  -0.0181   0.9239   0.9736
   2.000   0.3114   0.01133   0.00577  -0.0196   0.8855   0.9733
   2.250   0.3467   0.01099   0.00549  -0.0207   0.8466   0.9742
   2.500   0.3795   0.01098   0.00487  -0.0204   0.6554   0.9737
   2.750   0.3914   0.01259   0.00512  -0.0175   0.3552   0.9765
   3.000   0.4089   0.01392   0.00552  -0.0163   0.1460   0.9796
   3.250   0.4315   0.01468   0.00590  -0.0158   0.0658   0.9824
   3.500   0.4601   0.01525   0.00638  -0.0164   0.0348   0.9840
   3.750   0.4880   0.01587   0.00704  -0.0167   0.0238   0.9858
   4.000   0.5153   0.01656   0.00789  -0.0168   0.0194   0.9878
   4.250   0.5397   0.01774   0.00916  -0.0163   0.0166   0.9898
   4.500   0.5669   0.01830   0.00984  -0.0165   0.0138   0.9918
   4.750   0.5925   0.01941   0.01108  -0.0161   0.0126   0.9935
   5.000   0.6195   0.02069   0.01252  -0.0160   0.0116   0.9948
   5.250   0.6469   0.02222   0.01428  -0.0160   0.0110   0.9959
   5.500   0.6733   0.02411   0.01647  -0.0157   0.0107   0.9970
   5.750   0.6986   0.02644   0.01920  -0.0151   0.0105   0.9984
   6.000   0.7221   0.02928   0.02259  -0.0142   0.0104   0.9999
   6.250   0.7344   0.03219   0.02595  -0.0111   0.0105   1.0000
   6.500   0.7428   0.03502   0.02917  -0.0076   0.0104   1.0000
   6.750   0.7452   0.03803   0.03249  -0.0038   0.0098   1.0000
   7.000   0.7428   0.04198   0.03688   0.0010   0.0092   1.0000
   7.250   0.7475   0.04519   0.04042   0.0052   0.0085   1.0000
   7.500   0.7450   0.04889   0.04440   0.0097   0.0083   1.0000
   7.750   0.7394   0.05258   0.04833   0.0142   0.0083   1.0000
   8.000   0.7316   0.05617   0.05210   0.0186   0.0083   1.0000
   8.250   0.7214   0.05968   0.05578   0.0228   0.0083   1.0000
   8.500   0.7091   0.06309   0.05931   0.0268   0.0083   1.0000
   8.750   0.6946   0.06644   0.06276   0.0306   0.0084   1.0000
   9.000   0.6757   0.06936   0.06573   0.0347   0.0084   1.0000
   9.250   0.6563   0.07257   0.06898   0.0375   0.0085   1.0000
   9.500   0.6391   0.07680   0.07326   0.0376   0.0086   1.0000
   9.750   0.6252   0.08225   0.07872   0.0347   0.0087   1.0000
  10.000   0.6156   0.08866   0.08510   0.0298   0.0088   1.0000
  10.250   0.6090   0.09426   0.09066   0.0266   0.0089   1.0000
  10.500   0.6040   0.09953   0.09590   0.0241   0.0090   1.0000
  10.750   0.6000   0.10457   0.10090   0.0219   0.0091   1.0000
  11.000   0.5966   0.10946   0.10576   0.0200   0.0092   1.0000
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