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RAF 25 AIRFOIL (raf25-il)

RAF 25 AIRFOIL - RAF-25 airfoil


Airfoil raf25-il
Details Dat file Parser  
(raf25-il) RAF 25 AIRFOIL
RAF-25 airfoil
Max thickness 6.5% at 29.9% chord.
Max camber 1% at 49.9% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
RAF 25 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0121700 0.0096200
 0.0245200 0.0138500
 0.0493400 0.0191100
 0.0741700 0.0239700
 0.0990500 0.0274400
 0.1488600 0.0327700
 0.1987200 0.0369000
 0.2985100 0.0409800
 0.3985600 0.0416300
 0.4986400 0.0393000
 0.5987900 0.0347800
 0.6990300 0.0280600
 0.7993200 0.0197400
 0.8996200 0.0108200
 0.9497899 0.0061600
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0128200 -.0091600
 0.0254300 -.0123200
 0.0505600 -.0162500
 0.0756500 -.0187700
 0.1007200 -.0207100
 0.1507900 -.0227700
 0.2008300 -.0240300
 0.3008200 -.0237600
 0.4007600 -.0218900
 0.5006400 -.0184300
 0.6005100 -.0145600
 0.7003700 -.0107000
 0.8002500 -.0072300
 0.9001400 -.0039700
 0.9500800 -.0024300
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for RAF 25 AIRFOIL (raf25-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   raf25-il50,000928.3 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   raf25-il50,000530.6 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   raf25-il100,000943.3 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   raf25-il100,000540.2 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
   raf25-il200,000956.2 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   raf25-il200,000547.8 at α=2.25°Mach=0 Ncrit=5Xfoil predictionDetails
   raf25-il500,000968.2 at α=2°Mach=0 Ncrit=9Xfoil predictionDetails
   raf25-il500,000555.7 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   raf25-il1,000,000972.2 at α=1.25°Mach=0 Ncrit=9Xfoil predictionDetails
   raf25-il1,000,000568.1 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
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