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NACA 64-206 (naca64206-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 64-206 (naca64206-il)
Reynolds number: 100,000
Max Cl/Cd: 43.15 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca64206-il-100000.txt
Download as CSV file: xf-naca64206-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64-206                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.5668   0.09497   0.09024  -0.0117   1.0000   0.0682
  -8.000  -0.5718   0.09108   0.08639  -0.0191   1.0000   0.0686
  -7.750  -0.5751   0.08752   0.08272  -0.0260   1.0000   0.0690
  -7.500  -0.5549   0.08233   0.07765  -0.0144   1.0000   0.0748
  -7.250  -0.5513   0.07801   0.07333  -0.0190   1.0000   0.0783
  -7.000  -0.5506   0.07397   0.06904  -0.0294   1.0000   0.0819
  -6.750  -0.5415   0.06854   0.06376  -0.0278   1.0000   0.0849
  -6.500  -0.5305   0.06502   0.06022  -0.0282   1.0000   0.0910
  -6.250  -0.4800   0.04888   0.04441  -0.0287   1.0000   0.1039
  -6.000  -0.5077   0.05786   0.05241  -0.0357   1.0000   0.1094
  -5.750  -0.4943   0.05306   0.04794  -0.0335   1.0000   0.1157
  -5.500  -0.4795   0.04956   0.04430  -0.0345   1.0000   0.1297
  -5.250  -0.4643   0.04622   0.04076  -0.0356   1.0000   0.1517
  -4.250  -0.4172   0.03670   0.03168  -0.0263   1.0000   0.3278
  -4.000  -0.4044   0.03470   0.02981  -0.0224   1.0000   0.3735
  -3.750  -0.2996   0.02491   0.01625  -0.0350   1.0000   0.0678
  -3.500  -0.2739   0.02206   0.01307  -0.0341   1.0000   0.0632
  -3.250  -0.2477   0.02006   0.01074  -0.0329   1.0000   0.0609
  -3.000  -0.2228   0.01857   0.00910  -0.0319   1.0000   0.0648
  -2.750  -0.1984   0.01716   0.00760  -0.0308   1.0000   0.0709
  -2.500  -0.1753   0.01578   0.00631  -0.0297   1.0000   0.0758
  -2.250  -0.1520   0.01467   0.00519  -0.0286   1.0000   0.0851
  -2.000  -0.1278   0.01348   0.00420  -0.0281   1.0000   0.1278
  -1.750  -0.1041   0.01034   0.00406  -0.0224   1.0000   1.0000
  -1.500  -0.0887   0.01026   0.00370  -0.0209   1.0000   1.0000
  -1.250  -0.0683   0.01023   0.00344  -0.0203   1.0000   1.0000
  -1.000  -0.0462   0.01026   0.00326  -0.0199   1.0000   1.0000
  -0.750  -0.0236   0.01032   0.00316  -0.0196   1.0000   1.0000
  -0.500  -0.0008   0.01042   0.00311  -0.0192   1.0000   1.0000
  -0.250   0.0218   0.01055   0.00310  -0.0189   1.0000   1.0000
   0.000   0.0442   0.01071   0.00316  -0.0187   1.0000   1.0000
   0.250   0.0664   0.01090   0.00328  -0.0184   1.0000   1.0000
   0.500   0.0883   0.01113   0.00346  -0.0181   1.0000   1.0000
   0.750   0.1099   0.01139   0.00370  -0.0178   1.0000   1.0000
   1.000   0.1311   0.01169   0.00400  -0.0176   1.0000   1.0000
   1.250   0.1520   0.01204   0.00436  -0.0174   1.0000   1.0000
   1.500   0.1726   0.01243   0.00477  -0.0172   1.0000   1.0000
   1.750   0.2183   0.01294   0.00538  -0.0219   0.9892   1.0000
   2.000   0.2653   0.01343   0.00601  -0.0266   0.9784   1.0000
   2.250   0.3142   0.01386   0.00663  -0.0315   0.9663   1.0000
   2.500   0.3637   0.01415   0.00725  -0.0362   0.9518   1.0000
   2.750   0.4715   0.01196   0.00565  -0.0446   0.8679   1.0000
   3.000   0.4902   0.01136   0.00495  -0.0382   0.7541   1.0000
   3.250   0.4856   0.01512   0.00528  -0.0304   0.1118   1.0000
   3.500   0.5072   0.01674   0.00685  -0.0291   0.0841   1.0000
   3.750   0.5295   0.01832   0.00835  -0.0280   0.0716   1.0000
   4.000   0.5551   0.01961   0.00970  -0.0271   0.0625   1.0000
   4.250   0.5815   0.02189   0.01190  -0.0265   0.0593   1.0000
   4.500   0.6099   0.02453   0.01468  -0.0258   0.0588   1.0000
   4.750   0.6392   0.02644   0.01701  -0.0247   0.0607   1.0000
   5.000   0.6448   0.01667   0.00807  -0.0219   0.0591   1.0000
   5.250   0.6708   0.01929   0.01162  -0.0200   0.0665   1.0000
   9.000   0.7228   0.09871   0.09467  -0.0276   0.0970   1.0000
   9.250   0.7052   0.10448   0.10040  -0.0328   0.0966   1.0000
   9.500   0.6893   0.10973   0.10560  -0.0375   0.0952   1.0000
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