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NACA M15 AIRFOIL (m15-il)

NACA M15 AIRFOIL - NACA/Munk M-15 airfoil


Airfoil m15-il
Details Dat file Parser  
(m15-il) NACA M15 AIRFOIL
NACA/Munk M-15 airfoil
Max thickness 12% at 30% chord.
Max camber 3.8% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NACA M15 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0124500 0.0206300
 0.0249300 0.0303600
 0.0498900 0.0449200
 0.0748600 0.0564800
 0.0998400 0.0658400
 0.1498100 0.0795700
 0.1997800 0.0891900
 0.2997600 0.0983300
 0.3997600 0.0971800
 0.4997800 0.0899200
 0.5998100 0.0759700
 0.6998500 0.0592100
 0.7999000 0.0407600
 0.8999500 0.0214000
 0.9499700 0.0117300
 1.0000000 0.0022500

 0.0000000 0.0000000
 0.0125400 -.0162700
 0.0250500 -.0198400
 0.0500600 -.0226800
 0.0750600 -.0237200
 0.1000600 -.0238500
 0.1500600 -.0234300
 0.2000600 -.0227100
 0.3000500 -.0216600
 0.4000500 -.0220200
 0.5000600 -.0225700
 0.6000600 -.0226300
 0.7000500 -.0209800
 0.8000400 -.0180400
 0.9000300 -.0116900
 0.9500200 -.0073700
 1.0000000 -.0022500
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Lednicer format dat file
Selig format dat file

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Polars for NACA M15 AIRFOIL (m15-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   m15-il50,000923.8 at α=12°Mach=0 Ncrit=9Xfoil predictionDetails
   m15-il50,000530 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   m15-il100,000950.3 at α=9.75°Mach=0 Ncrit=9Xfoil predictionDetails
   m15-il100,000553.1 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   m15-il200,000972.2 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m15-il200,000572.3 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   m15-il500,0009101.6 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   m15-il500,000598.7 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   m15-il1,000,0009124.7 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m15-il1,000,0005118.5 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
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