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NACA M2 AIRFOIL (m2-il)

NACA M2 AIRFOIL - NACA/Munk M-2 airfoil


Airfoil m2-il
Details Dat file Parser  
(m2-il) NACA M2 AIRFOIL
NACA/Munk M-2 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 Lednicer format
NACA M2 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125000 0.0130000
 0.0250000 0.0174000
 0.0500000 0.0233000
 0.1000000 0.0284000
 0.1500000 0.0318000
 0.2000000 0.0349000
 0.2500000 0.0378000
 0.3000000 0.0400000
 0.4000000 0.0400000
 0.5000000 0.0374000
 0.6000000 0.0330000
 0.7000000 0.0271000
 0.8000000 0.0199000
 0.9000000 0.0115000
 0.9500000 0.0060000
 1.0000000 0.0020000

 0.0000000 0.0000000
 0.0125000 -.0130000
 0.0250000 -.0174000
 0.0500000 -.0233000
 0.1000000 -.0284000
 0.1500000 -.0318000
 0.2000000 -.0349000
 0.2500000 -.0378000
 0.3000000 -.0400000
 0.4000000 -.0400000
 0.5000000 -.0374000
 0.6000000 -.0330000
 0.7000000 -.0271000
 0.8000000 -.0199000
 0.9000000 -.0115000
 0.9500000 -.0060000
 1.0000000 -.0020000
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Lednicer format dat file
Selig format dat file

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Polars for NACA M2 AIRFOIL (m2-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   m2-il50,000921.8 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m2-il50,000521.6 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
   m2-il100,000929.4 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   m2-il100,000527.6 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   m2-il200,000932 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   m2-il200,000536.8 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   m2-il500,000945.9 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   m2-il500,000554.4 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   m2-il1,000,000960.6 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   m2-il1,000,000570.2 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
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