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NACA M16 AIRFOIL (m16-il)

NACA M16 AIRFOIL - NACA/Munk M-16 airfoil


Airfoil m16-il
Details Dat file Parser  
(m16-il) NACA M16 AIRFOIL
NACA/Munk M-16 airfoil
Max thickness 6.2% at 30% chord.
Max camber 4.1% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NACA M16 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125100 0.0120900
 0.0250100 0.0187900
 0.0500100 0.0297700
 0.0750200 0.0385600
 0.1000200 0.0458500
 0.1500300 0.0572200
 0.2000300 0.0650000
 0.3000400 0.0718500
 0.4000400 0.0700000
 0.5000300 0.0620500
 0.6000200 0.0497000
 0.7000200 0.0361500
 0.8000100 0.0227000
 0.9000100 0.0108500
 0.9500000 0.0061200
 1.0000000 0.0028000

 0.0000000 0.0000000
 0.0125000 -.0081100
 0.0250000 -.0082100
 0.0500000 -.0058200
 0.0750000 -.0032400
 0.1000000 -.0005500
 0.1500000 0.0040200
 0.2000000 0.0075000
 0.3000100 0.0103500
 0.4000000 0.0086000
 0.5000000 0.0044500
 0.6000000 -.0014000
 0.7000000 -.0060500
 0.8000000 -.0086000
 0.9000000 -.0074500
 0.9500000 -.0052700
 1.0000000 -.0028000
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Lednicer format dat file
Selig format dat file

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Polars for NACA M16 AIRFOIL (m16-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   m16-il50,000939 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   m16-il50,000538.1 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   m16-il100,000953.6 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   m16-il100,000553.6 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   m16-il200,000970.3 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m16-il200,000568.9 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   m16-il500,000992.7 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   m16-il500,000588.6 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   m16-il1,000,0009109.1 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m16-il1,000,0005102.9 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
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