Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NACA 0012-64 (naca001264-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 0012-64 (naca001264-il)
Reynolds number: 100,000
Max Cl/Cd: 37.76 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca001264-il-100000.txt
Download as CSV file: xf-naca001264-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0012-64                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.6733   0.09084   0.08556  -0.0274   1.0000   0.1925
  -9.750  -0.8391   0.06381   0.05764  -0.0309   1.0000   0.0999
  -9.500  -0.8427   0.05971   0.05343  -0.0284   1.0000   0.0981
  -9.250  -0.8531   0.05554   0.04900  -0.0247   1.0000   0.0956
  -9.000  -0.8936   0.05031   0.04266  -0.0156   1.0000   0.0885
  -8.750  -0.8881   0.04745   0.03950  -0.0124   1.0000   0.0879
  -8.500  -0.8824   0.04425   0.03600  -0.0094   1.0000   0.0876
  -8.250  -0.8773   0.04208   0.03342  -0.0058   1.0000   0.0881
  -8.000  -0.8673   0.03861   0.02979  -0.0036   1.0000   0.0896
  -7.750  -0.8531   0.03644   0.02748  -0.0016   1.0000   0.0911
  -7.500  -0.8380   0.03445   0.02528   0.0005   1.0000   0.0922
  -7.250  -0.8215   0.03264   0.02325   0.0025   1.0000   0.0935
  -7.000  -0.8042   0.03112   0.02152   0.0043   1.0000   0.0960
  -6.750  -0.7865   0.02977   0.01990   0.0063   1.0000   0.0990
  -6.500  -0.7678   0.02857   0.01837   0.0082   1.0000   0.1014
  -6.250  -0.7439   0.02666   0.01652   0.0088   1.0000   0.1046
  -6.000  -0.7224   0.02552   0.01537   0.0099   1.0000   0.1089
  -5.750  -0.7020   0.02465   0.01433   0.0114   1.0000   0.1148
  -5.500  -0.6805   0.02340   0.01323   0.0124   1.0000   0.1217
  -5.250  -0.6602   0.02254   0.01230   0.0140   1.0000   0.1305
  -5.000  -0.6418   0.02149   0.01141   0.0156   1.0000   0.1431
  -4.750  -0.6250   0.02052   0.01062   0.0175   1.0000   0.1624
  -4.500  -0.6098   0.01952   0.00987   0.0197   1.0000   0.1929
  -4.250  -0.5973   0.01823   0.00909   0.0222   1.0000   0.2505
  -4.000  -0.5915   0.01631   0.00843   0.0258   1.0000   0.4257
  -3.750  -0.5817   0.01541   0.00880   0.0306   1.0000   0.6658
  -3.500  -0.5635   0.01574   0.00939   0.0343   1.0000   0.7637
  -3.250  -0.5421   0.01639   0.01008   0.0375   1.0000   0.8194
  -3.000  -0.5167   0.01718   0.01079   0.0398   1.0000   0.8569
  -2.750  -0.4815   0.01807   0.01155   0.0401   1.0000   0.8840
  -2.500  -0.4381   0.01894   0.01225   0.0384   1.0000   0.9068
  -2.250  -0.3551   0.02029   0.01336   0.0294   1.0000   0.9275
  -2.000  -0.2713   0.02105   0.01392   0.0194   1.0000   0.9440
  -1.750  -0.1870   0.02143   0.01414   0.0088   1.0000   0.9615
  -1.500  -0.1117   0.02139   0.01399  -0.0008   1.0000   0.9781
  -1.250  -0.0605   0.02110   0.01363  -0.0065   1.0000   0.9884
  -1.000  -0.0097   0.02078   0.01326  -0.0122   1.0000   0.9978
  -0.750   0.0035   0.02062   0.01310  -0.0111   1.0000   1.0000
  -0.500   0.0026   0.02056   0.01303  -0.0075   1.0000   1.0000
  -0.250   0.0014   0.02052   0.01299  -0.0038   1.0000   1.0000
   0.000   0.0000   0.02051   0.01298   0.0000   1.0000   1.0000
   0.250  -0.0014   0.02052   0.01299   0.0038   1.0000   1.0000
   0.500  -0.0026   0.02056   0.01303   0.0075   1.0000   1.0000
   0.750  -0.0035   0.02062   0.01309   0.0111   1.0000   1.0000
   1.000   0.0096   0.02077   0.01325   0.0122   0.9978   1.0000
   1.250   0.0605   0.02110   0.01362   0.0065   0.9885   1.0000
   1.500   0.1116   0.02138   0.01398   0.0008   0.9781   1.0000
   1.750   0.1868   0.02142   0.01413  -0.0087   0.9616   1.0000
   2.000   0.2712   0.02104   0.01391  -0.0193   0.9440   1.0000
   2.250   0.3549   0.02028   0.01335  -0.0294   0.9275   1.0000
   2.500   0.4382   0.01894   0.01224  -0.0384   0.9069   1.0000
   2.750   0.4814   0.01807   0.01154  -0.0401   0.8841   1.0000
   3.000   0.5166   0.01718   0.01078  -0.0398   0.8569   1.0000
   3.250   0.5419   0.01639   0.01008  -0.0375   0.8194   1.0000
   3.500   0.5634   0.01573   0.00939  -0.0343   0.7639   1.0000
   3.750   0.5815   0.01540   0.00880  -0.0306   0.6660   1.0000
   4.000   0.5914   0.01631   0.00843  -0.0257   0.4261   1.0000
   4.250   0.5972   0.01823   0.00909  -0.0222   0.2507   1.0000
   4.500   0.6097   0.01951   0.00986  -0.0197   0.1930   1.0000
   4.750   0.6249   0.02052   0.01062  -0.0175   0.1624   1.0000
   5.000   0.6417   0.02149   0.01141  -0.0156   0.1431   1.0000
   5.250   0.6601   0.02254   0.01229  -0.0140   0.1305   1.0000
   5.500   0.6804   0.02339   0.01323  -0.0124   0.1217   1.0000
   5.750   0.7019   0.02464   0.01432  -0.0114   0.1148   1.0000
   6.000   0.7223   0.02552   0.01536  -0.0099   0.1089   1.0000
   6.250   0.7438   0.02666   0.01651  -0.0087   0.1046   1.0000
   6.500   0.7677   0.02856   0.01837  -0.0082   0.1014   1.0000
   6.750   0.7864   0.02977   0.01989  -0.0063   0.0990   1.0000
   7.000   0.8041   0.03112   0.02151  -0.0043   0.0960   1.0000
   7.250   0.8214   0.03264   0.02324  -0.0025   0.0935   1.0000
   7.500   0.8379   0.03445   0.02528  -0.0005   0.0922   1.0000
   7.750   0.8531   0.03644   0.02748   0.0016   0.0911   1.0000
   8.000   0.8672   0.03861   0.02978   0.0036   0.0896   1.0000
   8.250   0.8773   0.04207   0.03341   0.0058   0.0881   1.0000
   8.500   0.8823   0.04425   0.03600   0.0094   0.0876   1.0000
   8.750   0.8881   0.04745   0.03950   0.0124   0.0879   1.0000
   9.000   0.8935   0.05030   0.04266   0.0156   0.0885   1.0000
   9.250   0.8531   0.05555   0.04900   0.0247   0.0956   1.0000
   9.500   0.8428   0.05972   0.05343   0.0284   0.0981   1.0000
   9.750   0.8393   0.06383   0.05765   0.0308   0.0999   1.0000
  10.000   0.7009   0.06196   0.05652   0.0429   0.1139   1.0000
  10.250   0.6054   0.09996   0.09449   0.0172   0.1825   1.0000
<< Back to NACA 0012-64 (naca001264-il)

Polar data table (+)

Polar graphs


<< Back to NACA 0012-64 (naca001264-il)