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USA 31 AIRFOIL (usa31-il)

USA 31 AIRFOIL - USA-31 airfoil


Airfoil usa31-il
Details Dat file Parser  
(usa31-il) USA 31 AIRFOIL
USA-31 airfoil
Max thickness 14.8% at 19.7% chord.
Max camber 9.3% at 39.7% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
USA 31 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0118100 0.0342200
 0.0240000 0.0514400
 0.0485600 0.0758800
 0.0732700 0.0923200
 0.0980200 0.1057700
 0.1476700 0.1256700
 0.1974200 0.1395600
 0.2971700 0.1543600
 0.3971400 0.1561600
 0.4972800 0.1489600
 0.5975600 0.1337700
 0.6979500 0.1125700
 0.7984900 0.0833700
 0.8991800 0.0451900
 0.9496200 0.0211000
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0126900 -.0147700
 0.0252200 -.0165500
 0.0502500 -.0181000
 0.0752700 -.0186500
 0.1002500 -.0182000
 0.1501300 -.0144000
 0.2005900 -.0085400
 0.2999200 0.0122800
 0.3993900 0.0311900
 0.4994200 0.0299900
 0.5995200 0.0248000
 0.6996601 0.0176000
 0.7998200 0.0094000
 0.8999500 0.0022000
 0.9500100 -.0009000
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for USA 31 AIRFOIL (usa31-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   usa31-il50,00094.9 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   usa31-il50,000514.1 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   usa31-il100,000934.9 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   usa31-il100,000540.8 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   usa31-il200,000962.3 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   usa31-il200,000554.8 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   usa31-il500,000976.8 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   usa31-il500,000569.2 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   usa31-il1,000,000988.2 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   usa31-il1,000,000579.9 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
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