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RAF 15 AIRFOIL (raf15-il)

RAF 15 AIRFOIL - RAF-15 airfoil


Airfoil raf15-il
Details Dat file Parser  
(raf15-il) RAF 15 AIRFOIL
RAF-15 airfoil
Max thickness 6.5% at 15% chord.
Max camber 2.6% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
RAF 15 AIRFOIL
       16.       16.

 0.0000000 0.0000000
 0.0125000 0.0185800
 0.0250000 0.0255600
 0.0500000 0.0347100
 0.1000000 0.0459200
 0.1500000 0.0520300
 0.2000000 0.0552400
 0.3000000 0.0556600
 0.4000000 0.0531800
 0.5000000 0.0488000
 0.6000000 0.0433200
 0.7000000 0.0366400
 0.8000000 0.0284600
 0.9000000 0.0180800
 0.9500000 0.0119900
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0125000 -.0079200
 0.0250000 -.0104400
 0.0500000 -.0134900
 0.1000000 -.0147800
 0.1500000 -.0128700
 0.2000000 -.0090600
 0.3000000 -.0035400
 0.4000000 -.0029200
 0.5000000 -.0054000
 0.6000000 -.0085800
 0.7000000 -.0106600
 0.8000000 -.0097400
 0.9000000 -.0079200
 0.9500000 -.0065100
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for RAF 15 AIRFOIL (raf15-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   raf15-il50,000932.5 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   raf15-il50,000533.9 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   raf15-il100,000943.9 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   raf15-il100,000547.2 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   raf15-il200,000959.5 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   raf15-il200,000559.9 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   raf15-il500,000978.9 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   raf15-il500,000576.9 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   raf15-il1,000,000992.2 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   raf15-il1,000,000589.6 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
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