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NACA 64-208 (naca64208-il)

NACA 64-208 - NACA 64-208 airfoil


Airfoil naca64208-il
Details Dat file Parser  
(naca64208-il) NACA 64-208
NACA 64-208 airfoil
Max thickness 8% at 40% chord.
Max camber 1.1% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 64-208
1.00000     0.00000
0.95010     0.00522
0.90019     0.01067
0.85027     0.01634
0.80031     0.02200
0.75032     0.02749
0.70031     0.03263
0.65027     0.03733
0.60020     0.04152
0.55011     0.04506
0.50000     0.04787
0.44988     0.04978
0.39974     0.05063
0.34961     0.05009
0.29948     0.04856
0.24935     0.04598
0.19924     0.04232
0.14915     0.03741
0.09909     0.03089
0.07410     0.02681
0.04912     0.02189
0.02421     0.01549
0.01180     0.01110
0.00688     0.00862
0.00445     0.00706
0.00000     0.00000
0.00555     -0.00606
0.00812     -0.00722
0.01320     -0.00896
0.02579     -0.01177
0.05088     -0.01557
0.07590     -0.01833
0.10091     -0.02055
0.15085     -0.02395
0.20076     -0.02640
0.25065     -0.02808
0.30052     -0.02912
0.35039     -0.02949
0.40026     -0.02921
0.45012     -0.02788
0.50000     -0.02581
0.54989     -0.02316
0.59980     -0.02010
0.64973     -0.01673
0.69969     -0.01319
0.74968     -0.00959
0.79969     -0.00608
0.84973     -0.00288
0.89981     -0.00033
0.94990     0.00110
1.00000     0.00000
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Lednicer format dat file
Selig format dat file

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Polars for NACA 64-208 (naca64208-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca64208-il50,000926.6 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca64208-il50,000531.5 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   naca64208-il100,000945.3 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca64208-il100,000542.8 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca64208-il200,000958.9 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca64208-il200,000553.3 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
   naca64208-il500,000975.8 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca64208-il500,000560.7 at α=2.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca64208-il1,000,000980.8 at α=2.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca64208-il1,000,000570.1 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
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