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NACA M23 AIRFOIL (m23-il)

NACA M23 AIRFOIL - NACA/Munk M-23 airfoil


Airfoil m23-il
Details Dat file Parser  
(m23-il) NACA M23 AIRFOIL
NACA/Munk M-23 airfoil
Max thickness 8.1% at 30.1% chord.
Max camber 6.4% at 30.1% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NACA M23 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125900 0.0172300
 0.0251400 0.0274700
 0.0502300 0.0433400
 0.0752900 0.0560100
 0.1003500 0.0667800
 0.1504300 0.0833200
 0.2004900 0.0946600
 0.3005400 0.1045400
 0.4005300 0.1011200
 0.5004600 0.0882000
 0.6003600 0.0695800
 0.7002500 0.0484600
 0.8001500 0.0280400
 0.9000599 0.0119200
 0.9500300 0.0061600
 1.0000000 0.0027000

 0.0000000 0.0000000
 0.0124500 -.0086600
 0.0249600 -.0076300
 0.0499800 -.0035600
 0.0750100 0.0010100
 0.1000300 0.0056800
 0.1500700 0.0135200
 0.2001000 0.0188600
 0.3001200 0.0231400
 0.4001000 0.0198200
 0.5000600 0.0117000
 0.6000100 0.0021800
 0.6999600 -.0070400
 0.7999400 -.0124600
 0.8999400 -.0116800
 0.9499600 -.0082400
 1.0000000 -.0027000
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Lednicer format dat file
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Polars for NACA M23 AIRFOIL (m23-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   m23-il50,00096.9 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   m23-il50,000523.6 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   m23-il100,000944.6 at α=9.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m23-il100,000553.3 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   m23-il200,000976.5 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   m23-il200,000576 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   m23-il500,0009106.6 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   m23-il500,0005102.7 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   m23-il1,000,0009128.6 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   m23-il1,000,0005117.9 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
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