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USA 41 AIRFOIL (usa41-il)

USA 41 AIRFOIL - USA-41 airfoil


Airfoil usa41-il
Details Dat file Parser  
(usa41-il) USA 41 AIRFOIL
USA-41 airfoil
Max thickness 6.6% at 30% chord.
Max camber 4.5% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
USA 41 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125200 0.0155800
 0.0250400 0.0232600
 0.0500600 0.0352200
 0.0750700 0.0441800
 0.1000800 0.0518400
 0.1501000 0.0630600
 0.2001100 0.0703800
 0.3001200 0.0765200
 0.4001200 0.0753600
 0.5001100 0.0695000
 0.6001000 0.0609400
 0.7000800 0.0494800
 0.8000600 0.0353200
 0.9000300 0.0185600
 0.9500200 0.0100800
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0124900 -.0083200
 0.0249900 -.0090400
 0.0499800 -.0094800
 0.0749900 -.0088200
 0.0999900 -.0071600
 0.1500000 -.0019400
 0.2000100 0.0046800
 0.3000200 0.0105200
 0.4000200 0.0143600
 0.5000300 0.0171000
 0.6000300 0.0186400
 0.7000300 0.0167800
 0.8000200 0.0123200
 0.9000100 0.0055600
 0.9500000 0.0017800
 1.0000000 0.0000000
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Lednicer format dat file
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Polars for USA 41 AIRFOIL (usa41-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   usa41-il50,000941.2 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   usa41-il50,000542.2 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   usa41-il100,000959.8 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   usa41-il100,000560.9 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   usa41-il200,000979.3 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   usa41-il200,000579.9 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   usa41-il500,0009107.8 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   usa41-il500,0005104.6 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   usa41-il1,000,0009129.2 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   usa41-il1,000,0005122.8 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
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