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USA 29 AIRFOIL (usa29-il)

USA 29 AIRFOIL - USA-29 airfoil


Airfoil usa29-il
Details Dat file Parser  
(usa29-il) USA 29 AIRFOIL
USA-29 airfoil
Max thickness 13.2% at 29.7% chord.
Max camber 5.5% at 39.7% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
USA 29 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0120100 0.0178300
 0.0242400 0.0274700
 0.0487800 0.0441500
 0.0734000 0.0580300
 0.0980800 0.0695100
 0.1475900 0.0874700
 0.1972300 0.1003400
 0.2968500 0.1140900
 0.3968200 0.1152500
 0.4970300 0.1075200
 0.5974100 0.0937900
 0.6978800 0.0767600
 0.7985000 0.0544400
 0.8992100 0.0286200
 0.9496100 0.0142100
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0129600 -.0166400
 0.0256200 -.0224900
 0.0507400 -.0269000
 0.0758300 -.0299100
 0.1008400 -.0305200
 0.1508400 -.0303400
 0.2007600 -.0273600
 0.3004800 -.0175100
 0.4001100 -.0041600
 0.5000700 -.0026000
 0.6001400 -.0049400
 0.7002700 -.0096700
 0.8003200 -.0116100
 0.9002500 -.0090500
 0.9501700 -.0062800
 1.0000000 0.0000000
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Lednicer format dat file
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Polars for USA 29 AIRFOIL (usa29-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   usa29-il50,00096.6 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   usa29-il50,000527.1 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   usa29-il100,000950.4 at α=9.25°Mach=0 Ncrit=9Xfoil predictionDetails
   usa29-il100,000552.4 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   usa29-il200,000974.6 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   usa29-il200,000572.6 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   usa29-il500,000990 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   usa29-il500,000580.7 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   usa29-il1,000,0009101.1 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   usa29-il1,000,000595.5 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
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