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NACA 0012-34 (naca001234-il)

NACA 0012-34 - NACA 0012-34 airfoil


Airfoil naca001234-il
Details Dat file Parser  
(naca001234-il) NACA 0012-34
NACA 0012-34 airfoil
Max thickness 12% 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 0012-34
1.0000     0.00120
0.9500     0.01027
0.9000     0.01867
0.8000     0.03320
0.7000     0.04480
0.6000     0.05320
0.5000     0.05827
0.4000     0.06000
0.3000     0.05800
0.2000     0.05093
0.1500     0.04493
0.1000     0.03653
0.0750     0.03133
0.0500     0.02493
0.0250     0.01680
0.0125     0.01133
0.0000     0.00000
0.0125     -0.01133
0.0250     -0.01680
0.0500     -0.02493
0.0750     -0.03133
0.1000     -0.03653
0.1500     -0.04493
0.2000     -0.05093
0.3000     -0.05800
0.4000     -0.06000
0.5000     -0.05827
0.6000     -0.05320
0.7000     -0.04480
0.8000     -0.03320
0.9000     -0.01867
0.9500     -0.01027
1.0000     -0.00120
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Selig format dat file

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Polars for NACA 0012-34 (naca001234-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca001234-il50,000925.9 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca001234-il50,000527.5 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca001234-il100,000939.2 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   naca001234-il100,000536.7 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   naca001234-il200,000947.6 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca001234-il200,000539.7 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca001234-il500,000949.1 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca001234-il500,000545.6 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca001234-il1,000,000956.4 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   naca001234-il1,000,000555.7 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
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