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NACA M7 AIRFOIL (m7-il)

NACA M7 AIRFOIL - NACA/Munk M-7 airfoil


Airfoil m7-il
Details Dat file Parser  
(m7-il) NACA M7 AIRFOIL
NACA/Munk M-7 airfoil
Max thickness 6.2% at 40% chord.
Max camber 4.9% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NACA M7 AIRFOIL
       16.       16.

 0.0000000 0.0000000
 0.0125000 0.0203300
 0.0250000 0.0273700
 0.0500000 0.0385400
 0.0750000 0.0477100
 0.1000000 0.0554800
 0.1500000 0.0669200
 0.2000000 0.0747600
 0.3000000 0.0809400
 0.4000000 0.0772200
 0.5000000 0.0666000
 0.6000000 0.0519800
 0.7000000 0.0358600
 0.8000000 0.0207400
 0.9000000 0.0094200
 1.0000000 0.0047000

 0.0000000 0.0000000
 0.0125000 -.0001600
 0.0250000 0.0000700
 0.0500000 0.0025400
 0.0750000 0.0055100
 0.1000000 0.0075800
 0.1500000 0.0138200
 0.2000000 0.0171600
 0.3000000 0.0191400
 0.4000000 0.0153200
 0.5000000 0.0087000
 0.6000000 0.0005800
 0.7000000 -.0065400
 0.8000000 -.0105600
 0.9000000 -.0088800
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for NACA M7 AIRFOIL (m7-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   m7-il50,000934.2 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   m7-il50,000536 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   m7-il100,000950.3 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   m7-il100,000554.1 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   m7-il200,000963.5 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   m7-il200,000568.2 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   m7-il500,000973.1 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   m7-il500,000575.1 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   m7-il1,000,000973 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   m7-il1,000,000584 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
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