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NACA-0009 9.0% smoothed (n0009sm-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA-0009 9.0% smoothed (n0009sm-il)
Reynolds number: 50,000
Max Cl/Cd: 25.59 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n0009sm-il-50000-n5.txt
Download as CSV file: xf-n0009sm-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA-0009 9.0% smoothed                         
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.7052   0.09236   0.08512  -0.0179   1.0000   0.0549
 -10.750  -0.7211   0.08514   0.07791  -0.0227   1.0000   0.0547
 -10.500  -0.7400   0.07872   0.07148  -0.0268   1.0000   0.0545
 -10.250  -0.7592   0.07349   0.06619  -0.0289   1.0000   0.0542
 -10.000  -0.7814   0.06901   0.06161  -0.0289   1.0000   0.0541
  -9.750  -0.8024   0.06479   0.05718  -0.0278   1.0000   0.0543
  -9.500  -0.8195   0.06046   0.05250  -0.0263   1.0000   0.0549
  -9.250  -0.8115   0.05818   0.05031  -0.0252   1.0000   0.0578
  -9.000  -0.8100   0.05532   0.04727  -0.0237   1.0000   0.0603
  -8.750  -0.8118   0.05155   0.04313  -0.0219   1.0000   0.0620
  -8.500  -0.8104   0.04777   0.03887  -0.0199   1.0000   0.0638
  -8.250  -0.8068   0.04435   0.03477  -0.0176   1.0000   0.0671
  -8.000  -0.7934   0.04213   0.03248  -0.0163   1.0000   0.0715
  -7.750  -0.7791   0.03970   0.02974  -0.0147   1.0000   0.0754
  -7.500  -0.7631   0.03704   0.02656  -0.0131   1.0000   0.0788
  -7.250  -0.7453   0.03501   0.02430  -0.0118   1.0000   0.0839
  -7.000  -0.7263   0.03341   0.02249  -0.0105   1.0000   0.0905
  -6.750  -0.7045   0.03149   0.02019  -0.0093   1.0000   0.0954
  -6.500  -0.6826   0.02993   0.01859  -0.0083   1.0000   0.1006
  -6.250  -0.6608   0.02858   0.01703  -0.0072   1.0000   0.1092
  -6.000  -0.6398   0.02740   0.01579  -0.0060   1.0000   0.1191
  -5.750  -0.6182   0.02614   0.01452  -0.0048   1.0000   0.1280
  -5.500  -0.5969   0.02499   0.01331  -0.0035   1.0000   0.1394
  -5.250  -0.5768   0.02395   0.01226  -0.0022   1.0000   0.1585
  -5.000  -0.5569   0.02284   0.01127  -0.0010   1.0000   0.1842
  -4.750  -0.5376   0.02172   0.01035   0.0004   1.0000   0.2218
  -4.500  -0.5199   0.02064   0.00963   0.0019   1.0000   0.2844
  -4.250  -0.5026   0.01974   0.00907   0.0037   1.0000   0.3595
  -4.000  -0.4866   0.01901   0.00868   0.0061   1.0000   0.4351
  -3.750  -0.4702   0.01842   0.00836   0.0086   1.0000   0.5100
  -3.500  -0.4531   0.01795   0.00818   0.0114   1.0000   0.5859
  -3.250  -0.4338   0.01761   0.00811   0.0141   1.0000   0.6598
  -3.000  -0.4102   0.01743   0.00809   0.0163   1.0000   0.7274
  -2.750  -0.3798   0.01740   0.00807   0.0171   1.0000   0.7852
  -2.500  -0.3402   0.01751   0.00809   0.0161   1.0000   0.8338
  -2.250  -0.2955   0.01765   0.00807   0.0137   1.0000   0.8745
  -2.000  -0.2469   0.01779   0.00798   0.0102   1.0000   0.9084
  -1.750  -0.1932   0.01786   0.00785   0.0053   1.0000   0.9359
  -1.500  -0.1400   0.01780   0.00762   0.0001   1.0000   0.9605
  -1.250  -0.0872   0.01764   0.00730  -0.0053   1.0000   0.9832
  -1.000  -0.0393   0.01739   0.00695  -0.0102   1.0000   1.0000
  -0.750  -0.0297   0.01719   0.00674  -0.0077   1.0000   1.0000
  -0.500  -0.0199   0.01705   0.00658  -0.0052   1.0000   1.0000
  -0.250  -0.0100   0.01696   0.00649  -0.0026   1.0000   1.0000
   0.000   0.0000   0.01694   0.00646   0.0000   1.0000   1.0000
   0.250   0.0100   0.01696   0.00649   0.0026   1.0000   1.0000
   0.500   0.0199   0.01704   0.00658   0.0052   1.0000   1.0000
   0.750   0.0297   0.01718   0.00674   0.0077   1.0000   1.0000
   1.000   0.0393   0.01739   0.00695   0.0102   1.0000   1.0000
   1.250   0.0871   0.01763   0.00730   0.0054   0.9832   1.0000
   1.500   0.1399   0.01779   0.00762  -0.0001   0.9606   1.0000
   1.750   0.1931   0.01785   0.00785  -0.0053   0.9360   1.0000
   2.000   0.2470   0.01778   0.00798  -0.0102   0.9084   1.0000
   2.250   0.2955   0.01765   0.00806  -0.0137   0.8745   1.0000
   2.500   0.3402   0.01750   0.00808  -0.0161   0.8337   1.0000
   2.750   0.3797   0.01740   0.00807  -0.0171   0.7852   1.0000
   3.000   0.4102   0.01743   0.00809  -0.0163   0.7276   1.0000
   3.250   0.4337   0.01760   0.00811  -0.0141   0.6598   1.0000
   3.500   0.4530   0.01795   0.00818  -0.0114   0.5858   1.0000
   3.750   0.4701   0.01842   0.00836  -0.0086   0.5103   1.0000
   4.000   0.4865   0.01901   0.00868  -0.0060   0.4349   1.0000
   4.250   0.5025   0.01973   0.00907  -0.0037   0.3598   1.0000
   4.500   0.5198   0.02064   0.00963  -0.0019   0.2843   1.0000
   4.750   0.5375   0.02172   0.01035  -0.0003   0.2216   1.0000
   5.000   0.5569   0.02284   0.01127   0.0010   0.1839   1.0000
   5.250   0.5767   0.02394   0.01225   0.0023   0.1585   1.0000
   5.500   0.5969   0.02500   0.01332   0.0035   0.1394   1.0000
   5.750   0.6181   0.02615   0.01452   0.0048   0.1280   1.0000
   6.000   0.6397   0.02740   0.01579   0.0060   0.1190   1.0000
   6.250   0.6608   0.02859   0.01704   0.0072   0.1092   1.0000
   6.500   0.6825   0.02993   0.01858   0.0083   0.1006   1.0000
   6.750   0.7045   0.03149   0.02018   0.0093   0.0954   1.0000
   7.000   0.7264   0.03341   0.02249   0.0105   0.0905   1.0000
   7.250   0.7453   0.03500   0.02429   0.0118   0.0838   1.0000
   7.500   0.7631   0.03703   0.02655   0.0131   0.0788   1.0000
   7.750   0.7792   0.03971   0.02974   0.0147   0.0754   1.0000
   8.000   0.7935   0.04213   0.03247   0.0163   0.0714   1.0000
   8.250   0.8071   0.04436   0.03476   0.0176   0.0672   1.0000
   8.500   0.8104   0.04779   0.03889   0.0199   0.0638   1.0000
   8.750   0.8118   0.05159   0.04317   0.0219   0.0620   1.0000
   9.000   0.8103   0.05529   0.04724   0.0237   0.0602   1.0000
   9.250   0.8110   0.05830   0.05045   0.0252   0.0579   1.0000
   9.500   0.8195   0.06051   0.05255   0.0262   0.0548   1.0000
   9.750   0.8020   0.06486   0.05726   0.0277   0.0543   1.0000
  10.000   0.7821   0.06904   0.06163   0.0288   0.0541   1.0000
  10.250   0.7602   0.07349   0.06618   0.0288   0.0542   1.0000
  10.500   0.7394   0.07888   0.07164   0.0265   0.0544   1.0000
  10.750   0.7210   0.08528   0.07805   0.0225   0.0547   1.0000
  11.000   0.7050   0.09259   0.08535   0.0175   0.0549   1.0000
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