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NACA-M1 AIRFOIL (m1-il)

NACA-M1 AIRFOIL - NACA/Munk M-1 airfoil


Airfoil m1-il
Details Dat file Parser  
(m1-il) NACA-M1 AIRFOIL
NACA/Munk M-1 airfoil
Max thickness 6.2% at 30% chord.
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NACA-M1 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125000 0.0103000
 0.0250000 0.0136000
 0.0500000 0.0180000
 0.0750000 0.0210000
 0.1000000 0.0234000
 0.1500000 0.0267000
 0.2000000 0.0288000
 0.3000000 0.0308000
 0.4000000 0.0305000
 0.5000000 0.0285000
 0.6000000 0.0253000
 0.7000000 0.0208000
 0.8000000 0.0154000
 0.9000000 0.0091000
 0.9500000 0.0057000
 1.0000000 0.0020000

 0.0000000 0.0000000
 0.0125000 -.0103000
 0.0250000 -.0136000
 0.0500000 -.0180000
 0.0750000 -.0210000
 0.1000000 -.0234000
 0.1500000 -.0267000
 0.2000000 -.0288000
 0.3000000 -.0308000
 0.4000000 -.0305000
 0.5000000 -.0285000
 0.6000000 -.0253000
 0.7000000 -.0208000
 0.8000000 -.0154000
 0.9000000 -.0091000
 0.9500000 -.0057000
 1.0000000 -.0020000
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Lednicer format dat file
Selig format dat file

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Polars for NACA-M1 AIRFOIL (m1-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   m1-il50,000918.4 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   m1-il50,000520.6 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
   m1-il100,000927.6 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m1-il100,000524.9 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   m1-il200,000932.9 at α=2°Mach=0 Ncrit=9Xfoil predictionDetails
   m1-il200,000532.2 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   m1-il500,000938.2 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m1-il500,000550.5 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   m1-il1,000,000956 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   m1-il1,000,000563.4 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
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