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USA 40 AIRFOIL (usa40-il)

USA 40 AIRFOIL - USA-40 airfoil


Airfoil usa40-il
Details Dat file Parser  
(usa40-il) USA 40 AIRFOIL
USA-40 airfoil
Max thickness 13.3% at 30% chord.
Max camber 4.2% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
USA 40 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125100 0.0263000
 0.0250100 0.0360000
 0.0500100 0.0562900
 0.0750100 0.0686900
 0.1000200 0.0789800
 0.1500200 0.0935700
 0.2000200 0.1019600
 0.3000200 0.1071400
 0.4000200 0.1035200
 0.5000200 0.0949000
 0.6000200 0.0815800
 0.7000100 0.0655600
 0.8000100 0.0465400
 0.9000100 0.0251200
 0.9500000 0.0135100
 1.0000000 0.0005000

 0.0000000 0.0000000
 0.0125000 -.0190000
 0.0250000 -.0240100
 0.0499900 -.0287100
 0.0749900 -.0307200
 0.0999900 -.0320200
 0.1499900 -.0326300
 0.1999900 -.0307400
 0.2999900 -.0260600
 0.4000000 -.0196800
 0.5000000 -.0131000
 0.6000000 -.0058200
 0.7000000 0.0018600
 0.8000000 0.0075400
 0.9000000 0.0065200
 0.9500000 0.0031100
 1.0000000 -.0005000
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Lednicer format dat file
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Polars for USA 40 AIRFOIL (usa40-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   usa40-il50,000923.3 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   usa40-il50,000535.3 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   usa40-il100,000950.1 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   usa40-il100,000553.2 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   usa40-il200,000971.1 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   usa40-il200,000569.2 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   usa40-il500,000995.4 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   usa40-il500,000582.2 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   usa40-il1,000,0009105.1 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   usa40-il1,000,000587 at α=2.5°Mach=0 Ncrit=5Xfoil predictionDetails
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