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RAF 19 AIRFOIL (raf19-il)

RAF 19 AIRFOIL - RAF-19 airfoil


Airfoil raf19-il
Details Dat file Parser  
(raf19-il) RAF 19 AIRFOIL
RAF-19 airfoil
Max thickness 10.5% at 15% chord.
Max camber 10.1% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
RAF 19 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125000 0.0270700
 0.0250000 0.0461500
 0.0500000 0.0733000
 0.0750000 0.0924500
 0.1000000 0.1066000
 0.1500000 0.1259000
 0.2000000 0.1362000
 0.3000000 0.1418000
 0.4000000 0.1374000
 0.5000000 0.1250000
 0.6000000 0.1086000
 0.7000000 0.0872000
 0.8000000 0.0638000
 0.9000000 0.0364000
 0.9500000 0.0197000
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0125000 -.0080300
 0.0250000 -.0118500
 0.0500000 -.0107000
 0.0750000 -.0055500
 0.1000000 0.0026000
 0.1500000 0.0209000
 0.2000000 0.0382000
 0.3000000 0.0588000
 0.4000000 0.0654000
 0.5000000 0.0630000
 0.6000000 0.0536000
 0.7000000 0.0422000
 0.8000000 0.0268000
 0.9000000 0.0104000
 0.9500000 0.0017000
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for RAF 19 AIRFOIL (raf19-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   raf19-il50,000913.1 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   raf19-il50,000532.2 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   raf19-il100,000944.6 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   raf19-il100,000548.7 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   raf19-il200,000962.4 at α=9.25°Mach=0 Ncrit=9Xfoil predictionDetails
   raf19-il200,000561.8 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   raf19-il500,000982.2 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   raf19-il500,000583.3 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   raf19-il1,000,0009104.8 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   raf19-il1,000,0005103 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
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