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NACA M11 AIRFOIL (m11-il)

NACA M11 AIRFOIL - NACA/Munk M-11 airfoil


Airfoil m11-il
Details Dat file Parser  
(m11-il) NACA M11 AIRFOIL
NACA/Munk M-11 airfoil
Max thickness 8.2% at 30% chord.
Max camber 1.9% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NACA M11 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125000 0.0145700
 0.0250000 0.0210300
 0.0500000 0.0297700
 0.0750000 0.0363100
 0.1000000 0.0415400
 0.1500000 0.0494100
 0.2000000 0.0547800
 0.3000000 0.0595200
 0.4000000 0.0586600
 0.5000000 0.0535000
 0.6000000 0.0454400
 0.7000000 0.0351800
 0.8000000 0.0239200
 0.9000000 0.0120600
 0.9500000 0.0059300
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0125000 -.0120300
 0.0250000 -.0146700
 0.0500000 -.0175300
 0.0750000 -.0191900
 0.1000000 -.0200600
 0.1500000 -.0208900
 0.2000000 -.0214200
 0.3000000 -.0219800
 0.4000000 -.0221400
 0.5000000 -.0219000
 0.6000000 -.0207600
 0.7000000 -.0185200
 0.8000000 -.0146800
 0.9000000 -.0093400
 0.9500000 -.0062700
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for NACA M11 AIRFOIL (m11-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   m11-il50,000934.8 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   m11-il50,000535.2 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   m11-il100,000950.4 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m11-il100,000548.6 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   m11-il200,000965.7 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   m11-il200,000560.7 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   m11-il500,000984.8 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   m11-il500,000575.1 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   m11-il1,000,000996.6 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   m11-il1,000,000582.5 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
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