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NACA M22 AIRFOIL (m22-il)

NACA M22 AIRFOIL - NACA/Munk M-22 airfoil


Airfoil m22-il
Details Dat file Parser  
(m22-il) NACA M22 AIRFOIL
NACA/Munk M-22 airfoil
Max thickness 6.3% at 30% chord.
Max camber 6.3% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NACA M22 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125500 0.0138600
 0.0250800 0.0225200
 0.0501200 0.0371300
 0.0751600 0.0485500
 0.1002000 0.0590600
 0.1502500 0.0745000
 0.2002900 0.0852300
 0.3003200 0.0942900
 0.4003000 0.0908600
 0.5002600 0.0786200
 0.6002100 0.0613900
 0.7001400 0.0418500
 0.8000801 0.0237200
 0.9000300 0.0094800
 0.9500200 0.0049200
 1.0000000 0.0026500

 0.0000000 0.0000000
 0.0124800 -.0070400
 0.0249800 -.0050800
 0.0500000 0.0005300
 0.0750200 0.0063500
 0.1000400 0.0116600
 0.1500700 0.0207000
 0.2000900 0.0269300
 0.3001100 0.0317900
 0.4001000 0.0287600
 0.5000700 0.0199200
 0.6000300 0.0092900
 0.7000000 -.0011400
 0.7999700 -.0082800
 0.8999700 -.0096100
 0.9499800 -.0070800
 1.0000000 -.0026500
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Lednicer format dat file
Selig format dat file

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Polars for NACA M22 AIRFOIL (m22-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   m22-il50,000918.7 at α=12°Mach=0 Ncrit=9Xfoil predictionDetails
   m22-il50,000532.8 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   m22-il100,000954.6 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   m22-il100,000555.1 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   m22-il200,000974.9 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m22-il200,000573.9 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   m22-il500,0009100.3 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   m22-il500,000581.9 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   m22-il1,000,0009115 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m22-il1,000,000591 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
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