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NACA M12 AIRFOIL (m12-il)

NACA M12 AIRFOIL - NACA/Munk M-12 airfoil


Airfoil m12-il
Details Dat file Parser  
(m12-il) NACA M12 AIRFOIL
NACA/Munk M-12 airfoil
Max thickness 11.9% at 30% chord.
Max camber 2% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NACA M12 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125000 0.0203300
 0.0250000 0.0286500
 0.0500000 0.0403000
 0.0750000 0.0490500
 0.1000000 0.0561000
 0.1500000 0.0666000
 0.2000000 0.0734000
 0.3000000 0.0801000
 0.4000000 0.0794000
 0.5000000 0.0735000
 0.6000000 0.0639000
 0.7000000 0.0512000
 0.8000000 0.0366000
 0.9000000 0.0207000
 0.9500000 0.0126000
 1.0000000 0.0040000

 0.0000000 0.0000000
 0.0125000 -.0164800
 0.0250000 -.0213500
 0.0500000 -.0271000
 0.0750000 -.0305500
 0.1000000 -.0329000
 0.1500000 -.0357000
 0.2000000 -.0376000
 0.3000000 -.0392000
 0.4000000 -.0388000
 0.5000000 -.0372000
 0.6000000 -.0338000
 0.7000000 -.0286000
 0.8000000 -.0215000
 0.9000000 -.0119000
 0.9500000 -.0062000
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for NACA M12 AIRFOIL (m12-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   m12-il50,000931.6 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   m12-il50,000533.6 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   m12-il100,000949 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m12-il100,000548.8 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   m12-il200,000965.9 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m12-il200,000562.4 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   m12-il500,000986.7 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m12-il500,000577.2 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   m12-il1,000,000998.8 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m12-il1,000,000585.4 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
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