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USA 50 AIRFOIL (usa50-il)

USA 50 AIRFOIL - USA-50 airfoil


Airfoil usa50-il
Details Dat file Parser  
(usa50-il) USA 50 AIRFOIL
USA-50 airfoil
Max thickness 7% at 30% chord.
Max camber 2% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
USA 50 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125000 0.0100000
 0.0250000 0.0163000
 0.0500000 0.0247000
 0.0750000 0.0307000
 0.1000000 0.0360000
 0.1500000 0.0440000
 0.2000000 0.0490000
 0.3000000 0.0537000
 0.4000000 0.0540000
 0.5000000 0.0494000
 0.6000000 0.0440000
 0.7000000 0.0367000
 0.8000000 0.0280000
 0.9000000 0.0167000
 0.9500000 0.0100000
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0125000 -.0067000
 0.0250000 -.0097000
 0.0500000 -.0123000
 0.0750000 -.0133000
 0.1000000 -.0143000
 0.1500000 -.0157000
 0.2000000 -.0167000
 0.3000000 -.0167000
 0.4000000 -.0150000
 0.5000000 -.0130000
 0.6000000 -.0107000
 0.7000000 -.0083000
 0.8000000 -.0063000
 0.9000000 -.0040000
 0.9500000 -.0027000
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for USA 50 AIRFOIL (usa50-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   usa50-il50,000936.4 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   usa50-il50,000536.1 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   usa50-il100,000951.1 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   usa50-il100,000549.2 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   usa50-il200,000965.1 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   usa50-il200,000560.5 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
   usa50-il500,000980.4 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   usa50-il500,000573.3 at α=2.5°Mach=0 Ncrit=5Xfoil predictionDetails
   usa50-il1,000,000992.3 at α=2.25°Mach=0 Ncrit=9Xfoil predictionDetails
   usa50-il1,000,000583.7 at α=2°Mach=0 Ncrit=5Xfoil predictionDetails
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