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RAF 33 AIRFOIL (raf33-il)

RAF 33 AIRFOIL - RAF-33 airfoil


Airfoil raf33-il
Details Dat file Parser  
(raf33-il) RAF 33 AIRFOIL
RAF-33 airfoil
Max thickness 12.6% at 30% chord.
Max camber 4.7% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
RAF 33 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125500 0.0227700
 0.0250800 0.0339400
 0.0501200 0.0502800
 0.0751500 0.0629200
 0.1001800 0.0745600
 0.1502200 0.0910400
 0.2002400 0.1011200
 0.3002600 0.1100800
 0.4002600 0.1070400
 0.5002300 0.0940000
 0.6001800 0.0741600
 0.7001200 0.0519200
 0.8000700 0.0296800
 0.9000300 0.0114400
 0.9500100 0.0059200
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0124600 -.0150300
 0.0249600 -.0186600
 0.0499500 -.0207200
 0.0749500 -.0211800
 0.0999500 -.0208400
 0.1499500 -.0197600
 0.1999600 -.0184800
 0.2999600 -.0163200
 0.3999600 -.0173600
 0.4999500 -.0200000
 0.5999500 -.0220400
 0.6999500 -.0226800
 0.7999500 -.0209200
 0.8999700 -.0139600
 0.9499800 -.0088800
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for RAF 33 AIRFOIL (raf33-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   raf33-il50,00096.6 at α=-5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   raf33-il50,000519.4 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   raf33-il100,000939 at α=11.25°Mach=0 Ncrit=9Xfoil predictionDetails
   raf33-il100,000548.2 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   raf33-il200,000971.8 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   raf33-il200,000573.7 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   raf33-il500,0009107.7 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   raf33-il500,000599.2 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   raf33-il1,000,0009127.2 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   raf33-il1,000,0005110.4 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
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