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NACA 0012-64 (naca001264-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 0012-64 (naca001264-il)
Reynolds number: 50,000
Max Cl/Cd: 26.71 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca001264-il-50000.txt
Download as CSV file: xf-naca001264-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5400   0.11123   0.10337   0.0035   1.0000   0.3839
  -9.500  -0.6907   0.08123   0.07362  -0.0290   1.0000   0.1850
  -9.250  -0.7479   0.07408   0.06638  -0.0282   1.0000   0.1709
  -9.000  -0.8105   0.06813   0.05996  -0.0239   1.0000   0.1598
  -8.750  -0.8072   0.06393   0.05567  -0.0221   1.0000   0.1579
  -8.500  -0.8120   0.06014   0.05167  -0.0193   1.0000   0.1567
  -8.250  -0.8163   0.05658   0.04784  -0.0161   1.0000   0.1559
  -8.000  -0.8179   0.05320   0.04413  -0.0128   1.0000   0.1554
  -7.750  -0.8163   0.04995   0.04050  -0.0096   1.0000   0.1548
  -7.500  -0.8113   0.04686   0.03703  -0.0066   1.0000   0.1544
  -7.250  -0.8028   0.04403   0.03381  -0.0037   1.0000   0.1548
  -7.000  -0.7925   0.04157   0.03093  -0.0010   1.0000   0.1572
  -6.750  -0.7818   0.03947   0.02825   0.0020   1.0000   0.1605
  -6.500  -0.7609   0.03707   0.02593   0.0030   1.0000   0.1656
  -6.250  -0.7412   0.03507   0.02366   0.0046   1.0000   0.1705
  -6.000  -0.7209   0.03317   0.02144   0.0062   1.0000   0.1775
  -5.750  -0.6985   0.03156   0.01978   0.0073   1.0000   0.1889
  -5.500  -0.6726   0.02982   0.01806   0.0080   1.0000   0.2027
  -5.250  -0.6458   0.02820   0.01646   0.0086   1.0000   0.2245
  -5.000  -0.6180   0.02650   0.01509   0.0089   1.0000   0.2595
  -4.750  -0.5958   0.02462   0.01375   0.0102   1.0000   0.3210
  -4.500  -0.5899   0.02209   0.01272   0.0146   1.0000   0.4633
  -4.250  -0.5560   0.02403   0.01605   0.0234   1.0000   0.7793
  -4.000  -0.3987   0.02958   0.02056   0.0111   1.0000   0.8762
  -3.750  -0.2435   0.03068   0.02084  -0.0089   1.0000   0.9391
  -3.500  -0.1396   0.02934   0.01905  -0.0240   1.0000   0.9789
  -3.250  -0.0727   0.02778   0.01724  -0.0336   1.0000   1.0000
  -3.000  -0.0627   0.02716   0.01654  -0.0322   1.0000   1.0000
  -2.750  -0.0534   0.02661   0.01595  -0.0307   1.0000   1.0000
  -2.500  -0.0448   0.02614   0.01545  -0.0288   1.0000   1.0000
  -2.250  -0.0369   0.02574   0.01501  -0.0268   1.0000   1.0000
  -2.000  -0.0297   0.02539   0.01464  -0.0245   1.0000   1.0000
  -1.750  -0.0234   0.02511   0.01433  -0.0220   1.0000   1.0000
  -1.500  -0.0181   0.02487   0.01408  -0.0193   1.0000   1.0000
  -1.250  -0.0136   0.02468   0.01388  -0.0164   1.0000   1.0000
  -1.000  -0.0099   0.02453   0.01372  -0.0133   1.0000   1.0000
  -0.750  -0.0069   0.02442   0.01361  -0.0101   1.0000   1.0000
  -0.500  -0.0043   0.02434   0.01353  -0.0068   1.0000   1.0000
  -0.250  -0.0021   0.02430   0.01348  -0.0034   1.0000   1.0000
   0.000   0.0000   0.02428   0.01346   0.0000   1.0000   1.0000
   0.250   0.0021   0.02430   0.01348   0.0034   1.0000   1.0000
   0.500   0.0043   0.02434   0.01353   0.0068   1.0000   1.0000
   0.750   0.0069   0.02442   0.01361   0.0101   1.0000   1.0000
   1.000   0.0099   0.02453   0.01372   0.0133   1.0000   1.0000
   1.250   0.0136   0.02467   0.01387   0.0164   1.0000   1.0000
   1.500   0.0181   0.02486   0.01407   0.0193   1.0000   1.0000
   1.750   0.0234   0.02510   0.01432   0.0220   1.0000   1.0000
   2.000   0.0297   0.02539   0.01463   0.0245   1.0000   1.0000
   2.250   0.0369   0.02573   0.01500   0.0268   1.0000   1.0000
   2.500   0.0448   0.02613   0.01543   0.0288   1.0000   1.0000
   2.750   0.0534   0.02660   0.01594   0.0306   1.0000   1.0000
   3.000   0.0628   0.02714   0.01653   0.0322   1.0000   1.0000
   3.250   0.0728   0.02776   0.01722   0.0336   1.0000   1.0000
   3.500   0.1395   0.02932   0.01903   0.0240   0.9790   1.0000
   3.750   0.2436   0.03067   0.02082   0.0089   0.9392   1.0000
   4.000   0.3989   0.02957   0.02054  -0.0111   0.8762   1.0000
   4.250   0.5560   0.02402   0.01604  -0.0234   0.7794   1.0000
   4.500   0.5898   0.02208   0.01272  -0.0146   0.4637   1.0000
   4.750   0.5958   0.02461   0.01374  -0.0102   0.3211   1.0000
   5.000   0.6179   0.02649   0.01508  -0.0089   0.2596   1.0000
   5.250   0.6457   0.02819   0.01646  -0.0085   0.2246   1.0000
   5.500   0.6725   0.02982   0.01806  -0.0080   0.2028   1.0000
   5.750   0.6984   0.03156   0.01978  -0.0073   0.1889   1.0000
   6.000   0.7208   0.03317   0.02144  -0.0062   0.1775   1.0000
   6.250   0.7411   0.03507   0.02365  -0.0046   0.1706   1.0000
   6.500   0.7608   0.03707   0.02592  -0.0030   0.1656   1.0000
   6.750   0.7817   0.03947   0.02825  -0.0020   0.1605   1.0000
   7.000   0.7924   0.04157   0.03092   0.0010   0.1572   1.0000
   7.250   0.8027   0.04403   0.03380   0.0037   0.1548   1.0000
   7.500   0.8113   0.04686   0.03703   0.0066   0.1544   1.0000
   7.750   0.8162   0.04994   0.04050   0.0096   0.1548   1.0000
   8.000   0.8179   0.05319   0.04412   0.0128   0.1554   1.0000
   8.250   0.8163   0.05658   0.04783   0.0161   0.1559   1.0000
   8.500   0.8121   0.06014   0.05167   0.0193   0.1567   1.0000
   8.750   0.8073   0.06393   0.05567   0.0221   0.1579   1.0000
   9.000   0.8106   0.06813   0.05996   0.0239   0.1598   1.0000
   9.250   0.7482   0.07409   0.06639   0.0282   0.1709   1.0000
   9.500   0.6911   0.08127   0.07366   0.0289   0.1851   1.0000
   9.750   0.5411   0.11126   0.10340  -0.0037   0.3839   1.0000
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