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USA 25 AIRFOIL (usa25-il)

USA 25 AIRFOIL - USA-25 airfoil


Airfoil usa25-il
Details Dat file Parser  
(usa25-il) USA 25 AIRFOIL
USA-25 airfoil
Max thickness 8.3% at 19.9% chord.
Max camber 5.2% at 29.9% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
USA 25 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0123100 0.0178300
 0.0246900 0.0292600
 0.0495300 0.0445300
 0.0743700 0.0559400
 0.0993100 0.0652500
 0.1491800 0.0777800
 0.1990900 0.0863100
 0.2990100 0.0933700
 0.3990600 0.0887300
 0.4991400 0.0814900
 0.5992300 0.0723500
 0.6993600 0.0603100
 0.7995300 0.0446700
 0.8997300 0.0259400
 0.9498500 0.0137700
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0126300 -.0121700
 0.0251500 -.0138300
 0.0501600 -.0152700
 0.0751400 -.0135000
 0.1001100 -.0105400
 0.1500300 -.0032100
 0.1999600 0.0036200
 0.2998800 0.0113800
 0.3999000 0.0097400
 0.4999600 0.0042000
 0.6000300 -.0026400
 0.7000800 -.0070800
 0.8000801 -.0073200
 0.9000500 -.0042600
 0.9500200 -.0019300
 1.0000000 0.0000000
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Lednicer format dat file
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Polars for USA 25 AIRFOIL (usa25-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   usa25-il50,000925.6 at α=2.25°Mach=0 Ncrit=9Xfoil predictionDetails
   usa25-il50,000535.9 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   usa25-il100,000952.6 at α=9.75°Mach=0 Ncrit=9Xfoil predictionDetails
   usa25-il100,000554.6 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   usa25-il200,000974.1 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   usa25-il200,000573 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   usa25-il500,0009102 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   usa25-il500,000597.3 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   usa25-il1,000,0009124.6 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   usa25-il1,000,0005106.6 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
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