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NACA M5 AIRFOIL (m5-il)

NACA M5 AIRFOIL - NACA/Munk M-5 airfoil


Airfoil m5-il
Details Dat file Parser  
(m5-il) NACA M5 AIRFOIL
NACA/Munk M-5 airfoil
Max thickness 8.2% at 30.1% chord.
Max camber 2.1% at 30.1% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NACA M5 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0126300 0.0137800
 0.0251900 0.0201700
 0.0502700 0.0293300
 0.0753400 0.0367000
 0.1003900 0.0424700
 0.1504700 0.0511100
 0.2005300 0.0569500
 0.3005700 0.0617200
 0.4005600 0.0599900
 0.5004900 0.0533700
 0.6004000 0.0435500
 0.7003000 0.0323200
 0.8001900 0.0210000
 0.9001000 0.0105700
 0.9500600 0.0061100
 1.0000000 0.0031500

 0.0000000 0.0000000
 0.0123800 -.0125100
 0.0248500 -.0161300
 0.0498300 -.0184600
 0.0748200 -.0193900
 0.0998200 -.0198200
 0.1498200 -.0198900
 0.1998100 -.0200500
 0.2998100 -.0203700
 0.3998000 -.0219000
 0.4997800 -.0233200
 0.5997800 -.0242500
 0.6997800 -.0236700
 0.7998101 -.0204000
 0.8998700 -.0139200
 0.9499199 -.0087900
 1.0000000 -.0031500
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Lednicer format dat file
Selig format dat file

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Polars for NACA M5 AIRFOIL (m5-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   m5-il50,000932.7 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m5-il50,000534 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   m5-il100,000947.3 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   m5-il100,000546 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   m5-il200,000960.6 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   m5-il200,000557.2 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   m5-il500,000976.5 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   m5-il500,000570.1 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   m5-il1,000,000986.2 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   m5-il1,000,000576.7 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
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