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NACA 0010 (naca0010-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 0010 (naca0010-il)
Reynolds number: 200,000
Max Cl/Cd: 44.41 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca0010-il-200000.txt
Download as CSV file: xf-naca0010-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0010                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.7617   0.10155   0.09799   0.0000   1.0000   0.0494
 -11.500  -0.8675   0.07010   0.06617  -0.0236   1.0000   0.0379
 -11.250  -0.8918   0.06396   0.05989  -0.0267   1.0000   0.0375
 -11.000  -0.9154   0.05906   0.05480  -0.0272   1.0000   0.0373
 -10.750  -0.9373   0.05491   0.05041  -0.0254   1.0000   0.0371
 -10.500  -0.9524   0.05047   0.04564  -0.0236   1.0000   0.0371
 -10.250  -0.9607   0.04627   0.04103  -0.0215   1.0000   0.0374
 -10.000  -0.9614   0.04295   0.03725  -0.0193   1.0000   0.0380
  -9.750  -0.9624   0.03858   0.03237  -0.0171   1.0000   0.0392
  -9.500  -0.9494   0.03597   0.02968  -0.0162   1.0000   0.0410
  -9.250  -0.9324   0.03436   0.02796  -0.0152   1.0000   0.0428
  -9.000  -0.9169   0.03218   0.02546  -0.0138   1.0000   0.0446
  -8.750  -0.8995   0.03048   0.02341  -0.0124   1.0000   0.0470
  -8.500  -0.8824   0.02830   0.02084  -0.0109   1.0000   0.0491
  -8.250  -0.8622   0.02622   0.01871  -0.0102   1.0000   0.0516
  -8.000  -0.8405   0.02518   0.01757  -0.0094   1.0000   0.0545
  -7.750  -0.8182   0.02414   0.01635  -0.0084   1.0000   0.0575
  -7.500  -0.7953   0.02328   0.01523  -0.0075   1.0000   0.0595
  -7.250  -0.7736   0.02129   0.01323  -0.0067   1.0000   0.0629
  -7.000  -0.7508   0.02041   0.01233  -0.0059   1.0000   0.0660
  -6.750  -0.7276   0.01954   0.01137  -0.0050   1.0000   0.0689
  -6.500  -0.7041   0.01891   0.01062  -0.0041   1.0000   0.0718
  -6.250  -0.6833   0.01759   0.00935  -0.0030   1.0000   0.0755
  -6.000  -0.6614   0.01684   0.00861  -0.0019   1.0000   0.0795
  -5.750  -0.6391   0.01620   0.00790  -0.0008   1.0000   0.0843
  -5.500  -0.6189   0.01532   0.00712   0.0006   1.0000   0.0921
  -5.250  -0.5982   0.01456   0.00641   0.0018   1.0000   0.1048
  -5.000  -0.5782   0.01367   0.00571   0.0032   1.0000   0.1334
  -4.750  -0.5583   0.01280   0.00516   0.0044   1.0000   0.1879
  -4.500  -0.5375   0.01214   0.00480   0.0054   1.0000   0.2474
  -4.250  -0.5160   0.01162   0.00450   0.0065   1.0000   0.3041
  -4.000  -0.4944   0.01115   0.00428   0.0075   1.0000   0.3600
  -3.750  -0.4725   0.01075   0.00411   0.0085   1.0000   0.4151
  -3.500  -0.4503   0.01041   0.00397   0.0095   1.0000   0.4676
  -3.250  -0.4281   0.01008   0.00386   0.0106   1.0000   0.5230
  -3.000  -0.4060   0.00979   0.00381   0.0118   1.0000   0.5809
  -2.750  -0.3834   0.00955   0.00379   0.0129   1.0000   0.6323
  -2.500  -0.3604   0.00937   0.00378   0.0141   1.0000   0.6777
  -2.250  -0.3373   0.00923   0.00381   0.0152   1.0000   0.7208
  -2.000  -0.3143   0.00915   0.00387   0.0165   1.0000   0.7644
  -1.750  -0.2921   0.00912   0.00399   0.0180   1.0000   0.8068
  -1.500  -0.2705   0.00916   0.00416   0.0197   1.0000   0.8465
  -1.250  -0.2491   0.00928   0.00435   0.0214   1.0000   0.8838
  -1.000  -0.2245   0.00946   0.00457   0.0224   1.0000   0.9182
  -0.750  -0.1738   0.00969   0.00478   0.0180   0.9943   0.9431
  -0.500  -0.1201   0.00986   0.00492   0.0129   0.9881   0.9610
  -0.250  -0.0607   0.01000   0.00503   0.0066   0.9838   0.9715
   0.000   0.0000   0.01004   0.00506   0.0000   0.9778   0.9778
   0.250   0.0607   0.01000   0.00503  -0.0066   0.9715   0.9838
   0.500   0.1201   0.00986   0.00492  -0.0130   0.9609   0.9881
   0.750   0.1738   0.00969   0.00478  -0.0180   0.9431   0.9943
   1.000   0.2245   0.00946   0.00457  -0.0224   0.9181   1.0000
   1.250   0.2491   0.00928   0.00435  -0.0214   0.8838   1.0000
   1.500   0.2705   0.00916   0.00416  -0.0197   0.8465   1.0000
   1.750   0.2921   0.00912   0.00399  -0.0180   0.8068   1.0000
   2.000   0.3143   0.00915   0.00387  -0.0164   0.7643   1.0000
   2.250   0.3373   0.00923   0.00380  -0.0152   0.7208   1.0000
   2.500   0.3604   0.00936   0.00378  -0.0141   0.6778   1.0000
   2.750   0.3834   0.00955   0.00379  -0.0129   0.6324   1.0000
   3.000   0.4060   0.00979   0.00381  -0.0118   0.5811   1.0000
   3.250   0.4281   0.01008   0.00386  -0.0106   0.5230   1.0000
   3.500   0.4503   0.01041   0.00397  -0.0095   0.4676   1.0000
   3.750   0.4725   0.01075   0.00411  -0.0085   0.4152   1.0000
   4.000   0.4944   0.01115   0.00428  -0.0075   0.3601   1.0000
   4.250   0.5160   0.01162   0.00450  -0.0065   0.3041   1.0000
   4.500   0.5375   0.01214   0.00479  -0.0054   0.2474   1.0000
   4.750   0.5583   0.01280   0.00516  -0.0044   0.1879   1.0000
   5.000   0.5782   0.01367   0.00571  -0.0032   0.1333   1.0000
   5.250   0.5982   0.01456   0.00641  -0.0018   0.1048   1.0000
   5.500   0.6189   0.01532   0.00712  -0.0006   0.0922   1.0000
   5.750   0.6391   0.01620   0.00790   0.0007   0.0843   1.0000
   6.000   0.6614   0.01683   0.00861   0.0019   0.0795   1.0000
   6.250   0.6833   0.01759   0.00935   0.0030   0.0755   1.0000
   6.500   0.7041   0.01891   0.01062   0.0041   0.0718   1.0000
   6.750   0.7276   0.01954   0.01137   0.0050   0.0689   1.0000
   7.000   0.7508   0.02041   0.01233   0.0059   0.0660   1.0000
   7.250   0.7736   0.02129   0.01323   0.0067   0.0629   1.0000
   7.500   0.7953   0.02328   0.01523   0.0075   0.0595   1.0000
   7.750   0.8183   0.02413   0.01634   0.0084   0.0575   1.0000
   8.000   0.8405   0.02518   0.01757   0.0094   0.0545   1.0000
   8.250   0.8623   0.02622   0.01871   0.0102   0.0516   1.0000
   8.500   0.8825   0.02831   0.02085   0.0109   0.0491   1.0000
   8.750   0.8996   0.03049   0.02342   0.0123   0.0470   1.0000
   9.000   0.9169   0.03218   0.02546   0.0138   0.0446   1.0000
   9.250   0.9325   0.03436   0.02796   0.0152   0.0428   1.0000
   9.500   0.9495   0.03595   0.02966   0.0162   0.0409   1.0000
   9.750   0.9624   0.03860   0.03240   0.0171   0.0391   1.0000
  10.000   0.9615   0.04296   0.03725   0.0193   0.0380   1.0000
  10.250   0.9609   0.04628   0.04104   0.0214   0.0374   1.0000
  10.500   0.9526   0.05049   0.04566   0.0235   0.0371   1.0000
  10.750   0.9374   0.05494   0.05045   0.0253   0.0371   1.0000
  11.000   0.9156   0.05910   0.05485   0.0271   0.0372   1.0000
  11.250   0.8920   0.06403   0.05996   0.0265   0.0375   1.0000
  11.500   0.8678   0.07018   0.06626   0.0234   0.0379   1.0000
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