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NACA 66-210 (naca66210-il)

NACA 66-210 - NACA 66-210 airfoil


Airfoil naca66210-il
Details Dat file Parser  
(naca66210-il) NACA 66-210
NACA 66-210 airfoil
Max thickness 10% at 45% chord.
Max camber 1.1% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 66-210
1.00000     0.00000
0.95019     0.00724
0.90037     0.01570
0.85049     0.02445
0.80055     0.03289
0.75056     0.04071
0.70051     0.04759
0.65042     0.05332
0.60030     0.05736
0.55016     0.05960
0.50000     0.06074
0.44984     0.06095
0.39968     0.06024
0.34952     0.05862
0.29937     0.05608
0.24924     0.05257
0.19912     0.04796
0.14903     0.04202
0.09898     0.03432
0.07399     0.02958
0.04902     0.02401
0.02412     0.01699
0.01171     0.01245
0.00679     0.00980
0.00436     0.00806
0.00000     0.00000
0.00564     -0.00706
0.00821     -0.00840
0.01329     -0.01031
0.02588     -0.01327
0.05098     -0.01769
0.07601     -0.02110
0.10102     -0.02389
0.15097     -0.02856
0.20088     -0.03204
0.25076     -0.03467
0.30063     -0.03664
0.35048     -0.03802
0.40032     -0.03882
0.45016     -0.03905
0.50000     -0.03868
0.54984     -0.03770
0.59970     -0.03594
0.64958     -0.03272
0.69949     -0.02815
0.74944     -0.02281
0.79945     -0.01697
0.84951     -0.01099
0.89963     -0.00536
0.94981     -0.00092
1.00000     0.00000
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Lednicer format dat file
Selig format dat file

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Polars for NACA 66-210 (naca66210-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca66210-il50,000922.1 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca66210-il50,000527.6 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca66210-il100,000932.8 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   naca66210-il100,000536.7 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca66210-il200,000951.4 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca66210-il200,000546.7 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca66210-il500,000561.9 at α=2.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca66210-il500,000067.5 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   naca66210-il1,000,000982.2 at α=2.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca66210-il1,000,000567.1 at α=1.5°Mach=0 Ncrit=5Xfoil predictionDetails
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