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RAF 38 AIRFOIL (raf38-il)

RAF 38 AIRFOIL - RAF-38 airfoil


Airfoil raf38-il
Details Dat file Parser  
(raf38-il) RAF 38 AIRFOIL
RAF-38 airfoil
Max thickness 12.7% at 30% chord.
Max camber 2.5% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
RAF 38 AIRFOIL
       13.       13.

 0.0000000 0.0000000
 0.0250000 0.0298000
 0.0500000 0.0421000
 0.1000000 0.0594000
 0.2000000 0.0791000
 0.3000000 0.0875000
 0.4000000 0.0869000
 0.5000000 0.0806000
 0.6000000 0.0685000
 0.7000000 0.0527000
 0.8000000 0.0354000
 0.9000000 0.0183000
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0250000 -.0202000
 0.0500000 -.0266000
 0.1000000 -.0338000
 0.2000000 -.0386000
 0.3000000 -.0390000
 0.4000000 -.0366000
 0.5000000 -.0323000
 0.6000000 -.0273000
 0.7000000 -.0213000
 0.8000000 -.0146000
 0.9000000 -.0079000
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for RAF 38 AIRFOIL (raf38-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   raf38-il50,000931.6 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   raf38-il50,000532.5 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   raf38-il100,000951.6 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   raf38-il100,000551.9 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   raf38-il200,000971.5 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   raf38-il200,000569 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   raf38-il500,000996.6 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   raf38-il500,000590.5 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   raf38-il1,000,0009114.7 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   raf38-il1,000,000598.9 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
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