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NACA M10 AIRFOIL (m10-il)

NACA M10 AIRFOIL - NACA/Munk M-10 airfoil


Airfoil m10-il
Details Dat file Parser  
(m10-il) NACA M10 AIRFOIL
NACA/Munk M-10 airfoil
Max thickness 6.2% 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 M10 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0124900 0.0115100
 0.0249800 0.0163300
 0.0499700 0.0234600
 0.0749700 0.0290900
 0.0999600 0.0338100
 0.1499500 0.0407700
 0.1999500 0.0455300
 0.2999400 0.0500400
 0.3999400 0.0495600
 0.4999500 0.0453700
 0.5999600 0.0385900
 0.6999700 0.0302000
 0.7999800 0.0210200
 0.8999900 0.0116300
 0.9499900 0.0068900
 1.0000000 0.0019500

 0.0000000 0.0000000
 0.0125100 -.0092900
 0.0250100 -.0114700
 0.0500100 -.0129400
 0.0750200 -.0132100
 0.1000200 -.0131800
 0.1500100 -.0128300
 0.2000100 -.0123700
 0.3000100 -.0118500
 0.4000100 -.0120400
 0.5000100 -.0125200
 0.6000100 -.0126100
 0.7000100 -.0116900
 0.8000100 -.0097800
 0.9000100 -.0065600
 0.9500100 -.0044100
 1.0000000 -.0019500
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Lednicer format dat file
Selig format dat file

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Polars for NACA M10 AIRFOIL (m10-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   m10-il50,000934.4 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   m10-il50,000534.5 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   m10-il100,000946.5 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   m10-il100,000545.3 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   m10-il200,000958.8 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   m10-il200,000554.9 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   m10-il500,000972.9 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   m10-il500,000564.9 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
   m10-il1,000,000980.9 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   m10-il1,000,000575.3 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
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