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USA 35 A AIRFOIL (usa35a-il)

USA 35 A AIRFOIL - USA-35A airfoil


Airfoil usa35a-il
Details Dat file Parser  
(usa35a-il) USA 35 A AIRFOIL
USA-35A airfoil
Max thickness 18.2% at 29.4% chord.
Max camber 6.4% at 39.4% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
USA 35 A AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0109300 0.0380500
 0.0228000 0.0534400
 0.0468400 0.0769300
 0.0710700 0.0954200
 0.0955000 0.1094300
 0.1447100 0.1286500
 0.1941600 0.1418900
 0.2937000 0.1530900
 0.3937700 0.1515000
 0.4943000 0.1386400
 0.5950500 0.1202900
 0.6960300 0.0965400
 0.7971900 0.0683000
 0.8984800 0.0369700
 0.9491900 0.0196600
 1.0000000 0.0021500

 0.0000000 0.0000000
 0.0135900 -.0265400
 0.0263400 -.0326200
 0.0515200 -.0369800
 0.0765600 -.0379500
 0.1015700 -.0380200
 0.1515300 -.0370600
 0.2014100 -.0342100
 0.3011700 -.0284100
 0.4009200 -.0224000
 0.5006700 -.0162000
 0.6005000 -.0120900
 0.7003300 -.0079800
 0.8001800 -.0044700
 0.9001300 -.0030600
 0.9500901 -.0023000
 1.0000000 -.0021500
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Lednicer format dat file
Selig format dat file

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Polars for USA 35 A AIRFOIL (usa35a-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   usa35a-il50,00094.3 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   usa35a-il50,000520.4 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   usa35a-il100,000935.6 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   usa35a-il100,000546.4 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   usa35a-il200,000966.5 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   usa35a-il200,000567.1 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   usa35a-il500,000997.8 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   usa35a-il500,000592.3 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   usa35a-il1,000,0009122.3 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   usa35a-il1,000,0005109.6 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
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