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GOE 565 AIRFOIL (goe565-il)

GOE 565 AIRFOIL - Gottingen 565 airfoil


Airfoil goe565-il
Details Dat file Parser  
(goe565-il) GOE 565 AIRFOIL
Gottingen 565 airfoil
Max thickness 8.4% at 30% chord.
Max camber 2.8% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 565 AIRFOIL
       16.       16.

 0.0000000 0.0000000
 0.0125000 0.0166300
 0.0250000 0.0234500
 0.0500000 0.0341100
 0.0750000 0.0417600
 0.1000000 0.0479200
 0.1500000 0.0557300
 0.2000000 0.0615400
 0.3000000 0.0671600
 0.4000000 0.0677800
 0.5000000 0.0644000
 0.6000000 0.0580200
 0.7000000 0.0476400
 0.8000000 0.0347600
 0.9000000 0.0183800
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0125000 -.0113700
 0.0250000 -.0155400
 0.0500000 -.0183900
 0.0750000 -.0202300
 0.1000000 -.0205800
 0.1500000 -.0212700
 0.2000000 -.0209600
 0.3000000 -.0168400
 0.4000000 -.0127200
 0.5000000 -.0086000
 0.6000000 -.0044800
 0.7000000 -.0013600
 0.8000000 -.0007400
 0.9000000 -.0001200
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for GOE 565 AIRFOIL (goe565-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe565-il50,000937.4 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   goe565-il50,000539.1 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe565-il100,000956.9 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe565-il100,000555 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe565-il200,000976.2 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe565-il200,000569 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe565-il500,000998.7 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe565-il500,000580.7 at α=1.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe565-il1,000,0009110.1 at α=1.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe565-il1,000,000589.9 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
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