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NACA M4 AIRFOIL (m4-il)

NACA M4 AIRFOIL - NACA/Munk M-4 airfoil


Airfoil m4-il
Details Dat file Parser  
(m4-il) NACA M4 AIRFOIL
NACA/Munk M-4 airfoil
Max thickness 6.3% at 30% chord.
Max camber 2.2% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NACA M4 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125900 0.0121100
 0.0251300 0.0174100
 0.0501900 0.0253300
 0.0752400 0.0315400
 0.1002700 0.0365500
 0.1503300 0.0439800
 0.2003700 0.0491100
 0.3004000 0.0534600
 0.4003800 0.0516200
 0.5003400 0.0457700
 0.6002800 0.0369300
 0.7002000 0.0267800
 0.8001300 0.0169400
 0.9000599 0.0081900
 0.9500400 0.0048200
 1.0000000 0.0024500

 0.0000000 0.0000000
 0.0124300 -.0089900
 0.0249200 -.0105900
 0.0499200 -.0112700
 0.0749200 -.0113600
 0.0999200 -.0110400
 0.1499200 -.0101200
 0.1999300 -.0091900
 0.2999300 -.0093300
 0.3999200 -.0106800
 0.4999000 -.0129200
 0.5998900 -.0149700
 0.6998800 -.0161100
 0.7998900 -.0148600
 0.8999200 -.0106000
 0.9499500 -.0071800
 1.0000000 -.0024500
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Lednicer format dat file
Selig format dat file

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Polars for NACA M4 AIRFOIL (m4-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   m4-il50,000933.1 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m4-il50,000534 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   m4-il100,000945.5 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   m4-il100,000544.8 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   m4-il200,000957.3 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   m4-il200,000555.4 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   m4-il500,000971.9 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   m4-il500,000566.8 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   m4-il1,000,000980.7 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   m4-il1,000,000573.3 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
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