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USA 46 AIRFOIL (usa46-il)

USA 46 AIRFOIL - USA-46 airfoil


Airfoil usa46-il
Details Dat file Parser  
(usa46-il) USA 46 AIRFOIL
USA-46 airfoil
Max thickness 6.5% at 20% chord.
Max camber 2.2% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
USA 46 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0124800 0.0110200
 0.0249800 0.0170300
 0.0499600 0.0253700
 0.0749600 0.0321000
 0.0999500 0.0370400
 0.1499400 0.0448100
 0.1999300 0.0492800
 0.2999300 0.0524200
 0.3999300 0.0521600
 0.4999300 0.0477000
 0.5999400 0.0414400
 0.6999500 0.0332800
 0.7999700 0.0234200
 0.8999800 0.0125600
 0.9499900 0.0069300
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0125100 -.0099800
 0.0250200 -.0139600
 0.0500200 -.0176300
 0.0750300 -.0192900
 0.1000300 -.0198600
 0.1500300 -.0181900
 0.2000200 -.0161200
 0.3000200 -.0125800
 0.4000100 -.0088400
 0.5000100 -.0050000
 0.6000000 -.0011600
 0.7000000 0.0025800
 0.7999900 0.0057200
 0.9000000 0.0035600
 0.9500000 0.0013300
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for USA 46 AIRFOIL (usa46-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   usa46-il50,000938.3 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   usa46-il50,000538.3 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   usa46-il100,000952.9 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   usa46-il100,000551.8 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   usa46-il200,000969 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   usa46-il200,000563.6 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   usa46-il500,000986.4 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   usa46-il500,000575.1 at α=2.25°Mach=0 Ncrit=5Xfoil predictionDetails
   usa46-il1,000,000997.3 at α=2.25°Mach=0 Ncrit=9Xfoil predictionDetails
   usa46-il1,000,000580.8 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
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