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NACA M19 AIRFOIL (m19-il)

NACA M19 AIRFOIL - NACA/Munk M-19 airfoil


Airfoil m19-il
Details Dat file Parser  
(m19-il) NACA M19 AIRFOIL
NACA/Munk M-19 airfoil
Max thickness 6.2% at 30% chord.
Max camber 6% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NACA M19 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0124700 0.0129300
 0.0249500 0.0213600
 0.0499200 0.0356100
 0.0748900 0.0465700
 0.0998700 0.0566300
 0.1498400 0.0709400
 0.1998100 0.0817600
 0.2997900 0.0911900
 0.3998000 0.0888200
 0.4998200 0.0786500
 0.5998500 0.0632800
 0.6998900 0.0457100
 0.7999400 0.0280400
 0.8999700 0.0132700
 0.9499800 0.0070800
 1.0000000 0.0019000

 0.0000000 0.0000000
 0.0125200 -.0071700
 0.0250100 -.0054400
 0.0500000 -.0005800
 0.0749900 0.0047700
 0.0999800 0.0098300
 0.1499600 0.0182400
 0.1999400 0.0241600
 0.2999300 0.0294900
 0.3999400 0.0277200
 0.4999500 0.0210500
 0.5999700 0.0122800
 0.6999900 0.0037100
 0.8000100 -.0026600
 0.9000100 -.0052300
 0.9500100 -.0043100
 1.0000000 -.0019000
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Lednicer format dat file
Selig format dat file

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Polars for NACA M19 AIRFOIL (m19-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   m19-il50,000920.8 at α=11.25°Mach=0 Ncrit=9Xfoil predictionDetails
   m19-il50,000537.8 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   m19-il100,000957.8 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   m19-il100,000557.4 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   m19-il200,000977.4 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   m19-il200,000575.5 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   m19-il500,0009102.5 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   m19-il500,000583 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   m19-il1,000,0009117.9 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   m19-il1,000,000592.2 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
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