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NACA 63A210 (naca63a210-il)

NACA 63A210 - NACA 63A210 airfoil


Airfoil naca63a210-il
Details Dat file Parser  
(naca63a210-il) NACA 63A210
NACA 63A210 airfoil
Max thickness 10% at 34.9% chord.
Max camber 1.3% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 63A210
1.00000     0.00021
0.95026     0.00769
0.90050     0.01519
0.85072     0.02254
0.80074     0.02974
0.75061     0.03624
0.70052     0.04227
0.65041     0.04772
0.60028     0.05245
0.55012     0.05637
0.49994     0.05943
0.44975     0.06151
0.39955     0.06247
0.34935     0.06219
0.29916     0.06060
0.24898     0.05764
0.19882     0.05328
0.14869     0.04729
0.09863     0.03917
0.07364     0.03400
0.04869     0.02769
0.02384     0.01944
0.01151     0.01367
0.00664     0.01058
0.00423     0.00868
0.00000     0.00000
0.00577     -0.00756
0.00836     -0.00900
0.01349     -0.01125
0.02616     -0.01522
0.05131     -0.02047
0.07636     -0.02428
0.10137     -0.02725
0.15131     -0.03167
0.20118     -0.03468
0.25102     -0.03662
0.30084     -0.03764
0.35065     -0.03771
0.40045     -0.03689
0.45025     -0.03523
0.50006     -0.03283
0.54988     -0.02985
0.59972     -0.02641
0.64959     -0.02262
0.69948     -0.01861
0.74939     -0.01464
0.79926     -0.01104
0.84928     -0.00812
0.89950     -0.00539
0.94974     -0.00279
1.00000     -0.00021
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Lednicer format dat file
Selig format dat file

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Polars for NACA 63A210 (naca63a210-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca63a210-il50,000928.3 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca63a210-il50,000531.3 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca63a210-il100,000937.6 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca63a210-il100,000540.2 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca63a210-il200,000944.9 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   naca63a210-il200,000548.3 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca63a210-il500,000952 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca63a210-il500,000558.3 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   naca63a210-il1,000,000958.5 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca63a210-il1,000,000570.4 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
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