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NACA M13 AIRFOIL (m13-il)

NACA M13 AIRFOIL - NACA/Munk M-13 airfoil


Airfoil m13-il
Details Dat file Parser  
(m13-il) NACA M13 AIRFOIL
NACA/Munk M-13 airfoil
Max thickness 6.2% at 30% chord.
Max camber 3.8% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NACA M13 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125000 0.0127800
 0.0250000 0.0193700
 0.0500000 0.0296400
 0.0750000 0.0379100
 0.1000000 0.0446800
 0.1500000 0.0554200
 0.2000000 0.0627600
 0.3000000 0.0701400
 0.4000000 0.0694200
 0.5000000 0.0636000
 0.6000000 0.0537800
 0.7000000 0.0418600
 0.8000000 0.0292400
 0.9000000 0.0164200
 0.9500000 0.0105600
 1.0000000 0.0044000

 0.0000000 0.0000000
 0.0125000 -.0081200
 0.0250000 -.0081300
 0.0500000 -.0079100
 0.0750000 -.0043900
 0.1000000 -.0022200
 0.1500000 0.0019200
 0.2000000 0.0050600
 0.3000000 0.0080400
 0.4000000 0.0077200
 0.5000000 0.0055000
 0.6000000 0.0022800
 0.7000000 -.0006400
 0.8000000 -.0022600
 0.9000000 -.0022800
 0.9500000 -.0014400
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for NACA M13 AIRFOIL (m13-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   m13-il50,000938.8 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m13-il50,000540.6 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   m13-il100,000956.7 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   m13-il100,000556.8 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   m13-il200,000974.1 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m13-il200,000573.4 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   m13-il500,000998.1 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   m13-il500,000595 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   m13-il1,000,0009115.3 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m13-il1,000,000586.3 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
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