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NACA 0008-34 (naca000834-il)

NACA 0008-34 - NACA 0008-34 airfoil


Airfoil naca000834-il
Details Dat file Parser  
(naca000834-il) NACA 0008-34
NACA 0008-34 airfoil
Max thickness 8% at 40% chord.
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 0008-34
1.0000     0.00080
0.9500     0.00684
0.9000     0.01244
0.8000     0.02213
0.7000     0.02987
0.6000     0.03547
0.5000     0.03884
0.4000     0.04000
0.3000     0.03867
0.2000     0.03396
0.1500     0.02996
0.1000     0.02436
0.0750     0.02089
0.0500     0.01662
0.0250     0.01120
0.0125     0.00756
0.0000     0.00000
0.0125     -0.00756
0.0250     -0.01120
0.0500     -0.01662
0.0750     -0.02089
0.1000     -0.02436
0.1500     -0.02996
0.2000     -0.03396
0.3000     -0.03867
0.4000     -0.04000
0.5000     -0.03884
0.6000     -0.03547
0.7000     -0.02987
0.8000     -0.02213
0.9000     -0.01244
0.9500     -0.00684
1.0000     -0.00080
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Lednicer format dat file
Selig format dat file

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Polars for NACA 0008-34 (naca000834-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca000834-il50,000918.3 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca000834-il50,000518.5 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca000834-il100,000924.7 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   naca000834-il100,000530.1 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca000834-il200,000940.5 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca000834-il200,000536 at α=2.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca000834-il500,000957.2 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca000834-il500,000537.4 at α=2°Mach=0 Ncrit=5Xfoil predictionDetails
   naca000834-il1,000,000943 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca000834-il1,000,000542.8 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
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