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NASA/LANGLEY 64-012 AIRFOIL (n64012-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NASA/LANGLEY 64-012 AIRFOIL (n64012-il)
Reynolds number: 100,000
Max Cl/Cd: 32.85 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n64012-il-100000-n5.txt
Download as CSV file: xf-n64012-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY 64-012 AIRFOIL                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.7831   0.08140   0.07610  -0.0201   1.0000   0.0288
 -11.750  -0.8111   0.07422   0.06874  -0.0245   1.0000   0.0287
 -11.500  -0.8385   0.06822   0.06250  -0.0272   1.0000   0.0285
 -11.250  -0.8540   0.06415   0.05827  -0.0280   1.0000   0.0286
 -11.000  -0.8687   0.06052   0.05445  -0.0279   1.0000   0.0287
 -10.750  -0.8773   0.05770   0.05151  -0.0270   1.0000   0.0292
 -10.500  -0.8838   0.05514   0.04880  -0.0255   1.0000   0.0296
 -10.250  -0.8872   0.05252   0.04598  -0.0240   1.0000   0.0300
 -10.000  -0.8869   0.04983   0.04306  -0.0226   1.0000   0.0305
  -9.750  -0.8849   0.04685   0.03977  -0.0211   1.0000   0.0309
  -9.500  -0.8791   0.04390   0.03648  -0.0197   1.0000   0.0312
  -9.250  -0.8695   0.04112   0.03335  -0.0184   1.0000   0.0317
  -9.000  -0.8564   0.03855   0.03044  -0.0173   1.0000   0.0322
  -8.750  -0.8402   0.03619   0.02773  -0.0163   1.0000   0.0329
  -8.500  -0.8215   0.03405   0.02528  -0.0154   1.0000   0.0338
  -8.250  -0.8014   0.03233   0.02325  -0.0147   1.0000   0.0354
  -8.000  -0.7798   0.03051   0.02122  -0.0141   1.0000   0.0369
  -7.750  -0.7577   0.02883   0.01953  -0.0137   1.0000   0.0384
  -7.500  -0.7353   0.02741   0.01804  -0.0131   1.0000   0.0399
  -7.250  -0.7132   0.02612   0.01669  -0.0125   1.0000   0.0416
  -7.000  -0.6918   0.02497   0.01546  -0.0117   1.0000   0.0437
  -6.750  -0.6707   0.02407   0.01442  -0.0108   1.0000   0.0465
  -6.500  -0.6538   0.02288   0.01334  -0.0096   1.0000   0.0497
  -6.250  -0.6366   0.02200   0.01244  -0.0083   1.0000   0.0531
  -6.000  -0.6207   0.02124   0.01161  -0.0066   1.0000   0.0569
  -5.750  -0.6092   0.02045   0.01088  -0.0044   1.0000   0.0620
  -5.500  -0.5910   0.01978   0.01014  -0.0034   0.9947   0.0693
  -5.250  -0.5583   0.01878   0.00918  -0.0053   0.9821   0.0846
  -5.000  -0.5276   0.01759   0.00826  -0.0070   0.9700   0.1269
  -4.750  -0.5039   0.01573   0.00730  -0.0081   0.9573   0.2818
  -4.500  -0.4812   0.01464   0.00718  -0.0079   0.9452   0.4807
  -4.250  -0.4511   0.01455   0.00716  -0.0081   0.9347   0.5449
  -4.000  -0.4243   0.01463   0.00731  -0.0075   0.9230   0.5941
  -3.750  -0.3984   0.01490   0.00762  -0.0063   0.9119   0.6362
  -3.500  -0.3719   0.01519   0.00787  -0.0052   0.9019   0.6653
  -3.250  -0.3455   0.01532   0.00794  -0.0044   0.8915   0.6819
  -3.000  -0.3191   0.01525   0.00773  -0.0040   0.8809   0.6922
  -2.750  -0.2917   0.01523   0.00761  -0.0036   0.8718   0.6991
  -2.500  -0.2655   0.01515   0.00741  -0.0033   0.8619   0.7081
  -2.250  -0.2391   0.01512   0.00732  -0.0028   0.8524   0.7151
  -2.000  -0.2126   0.01502   0.00711  -0.0025   0.8443   0.7230
  -1.750  -0.1860   0.01499   0.00702  -0.0021   0.8345   0.7288
  -1.500  -0.1594   0.01491   0.00684  -0.0019   0.8263   0.7368
  -1.250  -0.1327   0.01488   0.00679  -0.0015   0.8174   0.7425
  -1.000  -0.1061   0.01483   0.00668  -0.0013   0.8094   0.7497
  -0.750  -0.0795   0.01480   0.00663  -0.0009   0.8015   0.7564
  -0.500  -0.0531   0.01479   0.00659  -0.0006   0.7935   0.7638
  -0.250  -0.0265   0.01476   0.00654  -0.0003   0.7858   0.7709
   0.000   0.0000   0.01476   0.00655   0.0000   0.7781   0.7780
   0.250   0.0266   0.01476   0.00654   0.0003   0.7709   0.7858
   0.500   0.0531   0.01479   0.00659   0.0006   0.7638   0.7935
   0.750   0.0796   0.01480   0.00663   0.0009   0.7563   0.8015
   1.000   0.1061   0.01483   0.00668   0.0013   0.7497   0.8094
   1.250   0.1327   0.01488   0.00679   0.0015   0.7425   0.8174
   1.500   0.1594   0.01491   0.00684   0.0019   0.7368   0.8264
   1.750   0.1860   0.01499   0.00702   0.0021   0.7288   0.8345
   2.000   0.2126   0.01502   0.00711   0.0025   0.7230   0.8443
   2.250   0.2391   0.01512   0.00732   0.0028   0.7151   0.8524
   2.500   0.2656   0.01515   0.00741   0.0032   0.7081   0.8619
   2.750   0.2917   0.01523   0.00761   0.0036   0.6991   0.8718
   3.000   0.3192   0.01525   0.00773   0.0040   0.6922   0.8809
   3.250   0.3455   0.01532   0.00794   0.0044   0.6819   0.8915
   3.500   0.3719   0.01519   0.00787   0.0052   0.6653   0.9019
   3.750   0.3984   0.01490   0.00762   0.0063   0.6361   0.9119
   4.000   0.4243   0.01463   0.00731   0.0075   0.5942   0.9230
   4.250   0.4511   0.01455   0.00716   0.0081   0.5449   0.9347
   4.500   0.4812   0.01465   0.00718   0.0079   0.4797   0.9452
   4.750   0.5038   0.01575   0.00730   0.0081   0.2796   0.9573
   5.000   0.5276   0.01759   0.00826   0.0070   0.1270   0.9700
   5.250   0.5583   0.01878   0.00918   0.0053   0.0845   0.9821
   5.500   0.5910   0.01978   0.01014   0.0034   0.0693   0.9948
   5.750   0.6092   0.02045   0.01088   0.0044   0.0620   1.0000
   6.000   0.6207   0.02124   0.01161   0.0066   0.0569   1.0000
   6.250   0.6366   0.02200   0.01243   0.0083   0.0531   1.0000
   6.500   0.6538   0.02288   0.01334   0.0096   0.0497   1.0000
   6.750   0.6708   0.02407   0.01442   0.0108   0.0465   1.0000
   7.000   0.6919   0.02497   0.01546   0.0117   0.0437   1.0000
   7.250   0.7133   0.02613   0.01669   0.0125   0.0416   1.0000
   7.500   0.7354   0.02742   0.01804   0.0131   0.0398   1.0000
   7.750   0.7578   0.02883   0.01953   0.0137   0.0384   1.0000
   8.000   0.7800   0.03053   0.02124   0.0140   0.0369   1.0000
   8.250   0.8015   0.03232   0.02324   0.0146   0.0354   1.0000
   8.500   0.8216   0.03405   0.02528   0.0154   0.0337   1.0000
   8.750   0.8404   0.03619   0.02773   0.0162   0.0329   1.0000
   9.000   0.8566   0.03855   0.03044   0.0172   0.0322   1.0000
   9.250   0.8697   0.04113   0.03336   0.0184   0.0317   1.0000
   9.500   0.8793   0.04391   0.03649   0.0196   0.0312   1.0000
   9.750   0.8851   0.04688   0.03981   0.0211   0.0309   1.0000
  10.000   0.8868   0.04993   0.04317   0.0226   0.0306   1.0000
  10.250   0.8868   0.05264   0.04612   0.0240   0.0300   1.0000
  10.500   0.8856   0.05504   0.04868   0.0254   0.0295   1.0000
  10.750   0.8798   0.05751   0.05128   0.0268   0.0290   1.0000
  11.000   0.8665   0.06083   0.05480   0.0278   0.0289   1.0000
  11.250   0.8547   0.06419   0.05831   0.0279   0.0286   1.0000
  11.500   0.8380   0.06840   0.06268   0.0270   0.0285   1.0000
  11.750   0.8150   0.07386   0.06835   0.0246   0.0286   1.0000
  12.000   0.7258   0.09393   0.08886   0.0104   0.0313   1.0000
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