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RAF 27 AIRFOIL (raf27-il)

RAF 27 AIRFOIL - RAF-27 airfoil


Airfoil raf27-il
Details Dat file Parser  
(raf27-il) RAF 27 AIRFOIL
RAF-27 airfoil
Max thickness 9.8% 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 27 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125000 0.0134000
 0.0250000 0.0190000
 0.0500000 0.0267000
 0.0750000 0.0320000
 0.1000000 0.0362000
 0.1500000 0.0424000
 0.2000000 0.0460000
 0.3000000 0.0488000
 0.4000000 0.0478000
 0.5000000 0.0437000
 0.6000000 0.0377000
 0.7000000 0.0296000
 0.8000000 0.0208000
 0.9000000 0.0112000
 0.9500000 0.0061000
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0125000 -.0134000
 0.0250000 -.0190000
 0.0500000 -.0267000
 0.0750000 -.0320000
 0.1000000 -.0362000
 0.1500000 -.0424000
 0.2000000 -.0460000
 0.3000000 -.0488000
 0.4000000 -.0478000
 0.5000000 -.0437000
 0.6000000 -.0377000
 0.7000000 -.0296000
 0.8000000 -.0208000
 0.9000000 -.0112000
 0.9500000 -.0061000
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for RAF 27 AIRFOIL (raf27-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   raf27-il50,000928.3 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   raf27-il50,000527.5 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   raf27-il100,000939.5 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   raf27-il100,000536.5 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   raf27-il200,000949.1 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   raf27-il200,000543.9 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   raf27-il500,000956.8 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   raf27-il500,000558.4 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   raf27-il1,000,000969.4 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   raf27-il1,000,000571.5 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
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