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RAF 69 AIRFOIL (raf69-il)

RAF 69 AIRFOIL - RAF-69 airfoil


Airfoil raf69-il
Details Dat file Parser  
(raf69-il) RAF 69 AIRFOIL
RAF-69 airfoil
Max thickness 20.6% at 30% chord.
Max camber 1.7% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
RAF 69 AIRFOIL
       13.       13.

 0.0000000 0.0000000
 0.0250000 0.0414800
 0.0500000 0.0609600
 0.1000000 0.0849300
 0.2000000 0.1096600
 0.3000000 0.1186900
 0.4000000 0.1171200
 0.5000000 0.1082500
 0.6000000 0.0927800
 0.7000000 0.0724100
 0.8000000 0.0490400
 0.9000000 0.0243700
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0250000 -.0374200
 0.0500000 -.0526400
 0.1000000 -.0705700
 0.2000000 -.0855400
 0.3000000 -.0877100
 0.4000000 -.0831800
 0.5000000 -.0739500
 0.6000000 -.0615200
 0.7000000 -.0464900
 0.8000000 -.0297600
 0.9000000 -.0148300
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for RAF 69 AIRFOIL (raf69-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   raf69-il50,00094.7 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   raf69-il50,000518.7 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   raf69-il100,000940.3 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   raf69-il100,000540.1 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   raf69-il200,000958.2 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   raf69-il200,000551.7 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   raf69-il500,000974 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   raf69-il500,000563.9 at α=8.75°Mach=0 Ncrit=5Xfoil predictionDetails
   raf69-il1,000,000988.1 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   raf69-il1,000,000572.4 at α=9.75°Mach=0 Ncrit=5Xfoil predictionDetails
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