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RAF 26 AIRFOIL (raf26-il)

RAF 26 AIRFOIL - RAF-26 airfoil


Airfoil raf26-il
Details Dat file Parser  
(raf26-il) RAF 26 AIRFOIL
RAF-26 airfoil
Max thickness 6.6% at 29.9% chord.
Max camber 2.1% at 49.9% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
RAF 26 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0122800 0.0107500
 0.0246700 0.0162100
 0.0495300 0.0231200
 0.0744400 0.0275300
 0.0993400 0.0324400
 0.1492000 0.0391600
 0.1991000 0.0440800
 0.2989600 0.0507300
 0.3989500 0.0518200
 0.4989500 0.0510300
 0.5990600 0.0458800
 0.6992100 0.0383300
 0.7994200 0.0282900
 0.8996601 0.0166400
 0.9497899 0.0104700
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0126500 -.0075400
 0.0252100 -.0104800
 0.0502800 -.0137700
 0.0753200 -.0154600
 0.1003400 -.0164400
 0.1503600 -.0174200
 0.2003500 -.0172900
 0.3003200 -.0154400
 0.4002400 -.0118000
 0.5001700 -.0082500
 0.6001000 -.0051000
 0.7000500 -.0025500
 0.8000200 -.0010000
 0.9000100 -.0006500
 0.9500300 -.0012200
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for RAF 26 AIRFOIL (raf26-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   raf26-il50,000934 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   raf26-il50,000537.1 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   raf26-il100,000953.8 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   raf26-il100,000551.2 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   raf26-il200,000971.3 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   raf26-il200,000562.1 at α=2.5°Mach=0 Ncrit=5Xfoil predictionDetails
   raf26-il500,000988.8 at α=2°Mach=0 Ncrit=9Xfoil predictionDetails
   raf26-il500,000569.8 at α=1.25°Mach=0 Ncrit=5Xfoil predictionDetails
   raf26-il1,000,000994.1 at α=1.25°Mach=0 Ncrit=9Xfoil predictionDetails
   raf26-il1,000,000576.8 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
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