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NACA 0008 (naca0008-il)

NACA 0008 - NACA 0008 airfoil


Airfoil naca0008-il
Details Dat file Parser  
(naca0008-il) NACA 0008
NACA 0008 airfoil
Max thickness 8% at 30% chord.
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 0008
1.0000     0.00084
0.9500     0.00537
0.9000     0.00965
0.8000     0.01749
0.7000     0.02443
0.6000     0.03043
0.5000     0.03529
0.4000     0.03869
0.3000     0.04001
0.2500     0.03961
0.2000     0.03825
0.1500     0.03564
0.1000     0.03121
0.0750     0.02800
0.0500     0.02369
0.0250     0.01743
0.0125     0.01263
0.0000     0.00000
0.0125     -0.01263
0.0250     -0.01743
0.0500     -0.02369
0.0750     -0.02800
0.1000     -0.03121
0.1500     -0.03564
0.2000     -0.03825
0.2500     -0.03961
0.3000     -0.04001
0.4000     -0.03869
0.5000     -0.03529
0.6000     -0.03043
0.7000     -0.02443
0.8000     -0.01749
0.9000     -0.00965
0.9500     -0.00537
1.0000     -0.00084
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Selig format dat file

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Polars for NACA 0008 (naca0008-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca0008-il50,000926.1 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   naca0008-il50,000524.6 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca0008-il100,000934.6 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca0008-il100,000530.4 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca0008-il200,000941.1 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca0008-il200,000538.5 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca0008-il500,000950.2 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca0008-il500,000556.2 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   naca0008-il1,000,000968.3 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca0008-il1,000,000569.9 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
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