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NACA M24 AIRFOIL (m24-il)

NACA M24 AIRFOIL - NACA/Munk M-24 airfoil


Airfoil m24-il
Details Dat file Parser  
(m24-il) NACA M24 AIRFOIL
NACA/Munk M-24 airfoil
Max thickness 12% at 30.1% chord.
Max camber 6.3% at 30.1% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NACA M24 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0127000 0.0228900
 0.0253000 0.0347800
 0.0504700 0.0537600
 0.0755900 0.0681500
 0.1007000 0.0807300
 0.1508600 0.0996000
 0.2009700 0.1125600
 0.3010700 0.1232000
 0.4010300 0.1191300
 0.5009100 0.1046700
 0.6007200 0.0837000
 0.7005200 0.0600400
 0.8003100 0.0362800
 0.9001400 0.0157100
 0.9500700 0.0076800
 1.0000000 0.0023500

 0.0000000 0.0000000
 0.0123800 -.0139100
 0.0248700 -.0151200
 0.0498800 -.0141300
 0.0749000 -.0116500
 0.0999300 -.0086600
 0.1499700 -.0032000
 0.2000100 0.0009700
 0.3000300 0.0037000
 0.4000100 0.0007400
 0.4999500 -.0060200
 0.5998800 -.0137900
 0.6998300 -.0197500
 0.7998101 -.0215200
 0.8998600 -.0164800
 0.9499100 -.0106200
 1.0000000 -.0023500
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Lednicer format dat file
Selig format dat file

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Polars for NACA M24 AIRFOIL (m24-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   m24-il50,00095.1 at α=9°Mach=0 Ncrit=9Xfoil predictionDetails
   m24-il50,000519.9 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   m24-il100,000925.5 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   m24-il100,000545.2 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   m24-il200,000967.9 at α=10.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m24-il200,000571.2 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   m24-il500,0009104.2 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   m24-il500,0005100.6 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
   m24-il1,000,0009129.3 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   m24-il1,000,0005118.9 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
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