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RAF 30 AIRFOIL (raf30-il)

RAF 30 AIRFOIL - RAF-30 airfoil


Airfoil raf30-il
Details Dat file Parser  
(raf30-il) RAF 30 AIRFOIL
RAF-30 airfoil
Max thickness 12.6% at 30% chord.
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
RAF 30 AIRFOIL
       16.       16.

 0.0000000 0.0000000
 0.0125000 0.0180000
 0.0250000 0.0248000
 0.0500000 0.0346000
 0.1000000 0.0468000
 0.1500000 0.0544000
 0.2000000 0.0594000
 0.3000000 0.0632000
 0.4000000 0.0620000
 0.5000000 0.0566000
 0.6000000 0.0478000
 0.7000000 0.0370000
 0.8000000 0.0250000
 0.9000000 0.0130000
 0.9500000 0.0070000
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0125000 -.0180000
 0.0250000 -.0248000
 0.0500000 -.0346000
 0.1000000 -.0468000
 0.1500000 -.0544000
 0.2000000 -.0594000
 0.3000000 -.0632000
 0.4000000 -.0620000
 0.5000000 -.0566000
 0.6000000 -.0478000
 0.7000000 -.0370000
 0.8000000 -.0250000
 0.9000000 -.0130000
 0.9500000 -.0070000
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for RAF 30 AIRFOIL (raf30-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   raf30-il50,000928.4 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   raf30-il50,000528.7 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   raf30-il100,000941.7 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   raf30-il100,000539.1 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   raf30-il200,000952.3 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   raf30-il200,000545.6 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   raf30-il500,000958.5 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   raf30-il500,000558.3 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   raf30-il1,000,000969.5 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   raf30-il1,000,000571.6 at α=9°Mach=0 Ncrit=5Xfoil predictionDetails
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