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RAF 34 AIRFOIL (raf34-il)

RAF 34 AIRFOIL - RAF-34 airfoil


Airfoil raf34-il
Details Dat file Parser  
(raf34-il) RAF 34 AIRFOIL
RAF-34 airfoil
Max thickness 12.6% at 30% chord.
Max camber 2% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
RAF 34 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125000 0.0196000
 0.0250000 0.0282000
 0.0500000 0.0411000
 0.0750000 0.0512000
 0.1000000 0.0583000
 0.1500000 0.0697000
 0.2000000 0.0772000
 0.3000000 0.0832000
 0.4000000 0.0808000
 0.5000000 0.0721000
 0.6000000 0.0587000
 0.7000000 0.0431000
 0.8000000 0.0270000
 0.9000000 0.0126000
 0.9500000 0.0064000
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0125000 -.0162000
 0.0250000 -.0214000
 0.0500000 -.0281000
 0.0750000 -.0325000
 0.1000000 -.0353000
 0.1500000 -.0391000
 0.2000000 -.0416000
 0.3000000 -.0432000
 0.4000000 -.0432000
 0.5000000 -.0411000
 0.6000000 -.0369000
 0.7000000 -.0309000
 0.8000000 -.0230000
 0.9000000 -.0134000
 0.9500000 -.0076000
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for RAF 34 AIRFOIL (raf34-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   raf34-il50,000925.7 at α=10.5°Mach=0 Ncrit=9Xfoil predictionDetails
   raf34-il50,000530.7 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   raf34-il100,000948.2 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   raf34-il100,000549.1 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   raf34-il200,000967.5 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   raf34-il200,000565.2 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   raf34-il500,000990.8 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   raf34-il500,000579.4 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   raf34-il1,000,000999.8 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   raf34-il1,000,000584.8 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
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