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RAF 6 AIRFOIL (raf6-il)

RAF 6 AIRFOIL - RAF-6 airfoil


Airfoil raf6-il
Details Dat file Parser  
(raf6-il) RAF 6 AIRFOIL
RAF-6 airfoil
Max thickness 10% at 30% chord.
Max camber 4.6% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
RAF 6 AIRFOIL
       13.       13.

 0.0000000 0.0000000
 0.0248700 0.0359900
 0.0498100 0.0540800
 0.0997300 0.0742600
 0.1996700 0.0906200
 0.2996600 0.0957800
 0.3996600 0.0953400
 0.4996700 0.0917000
 0.5997000 0.0840600
 0.6997400 0.0714200
 0.7998101 0.0537800
 0.8998800 0.0331400
 1.0000000 0.0015000

 0.0000000 0.0000000
 0.0250200 -.0050100
 0.0500200 -.0049200
 0.1000200 -.0047400
 0.2000200 -.0043800
 0.3000100 -.0040200
 0.4000100 -.0036600
 0.5000100 -.0033000
 0.6000100 -.0029400
 0.7000100 -.0025800
 0.8000100 -.0022200
 0.9000100 -.0018600
 1.0000000 -.0015000
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Lednicer format dat file
Selig format dat file

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Polars for RAF 6 AIRFOIL (raf6-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   raf6-il50,000935.7 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   raf6-il50,000536.7 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   raf6-il100,000951.9 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   raf6-il100,000552.5 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
   raf6-il200,000970.3 at α=2°Mach=0 Ncrit=9Xfoil predictionDetails
   raf6-il200,000568.2 at α=1.25°Mach=0 Ncrit=5Xfoil predictionDetails
   raf6-il500,000990.5 at α=0.75°Mach=0 Ncrit=9Xfoil predictionDetails
   raf6-il500,000585 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   raf6-il1,000,0009104.8 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   raf6-il1,000,0005105 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
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