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GOE 6K AIRFOIL (goe06k-il)

GOE 6K AIRFOIL - Gottingen 6K airfoil


Airfoil goe06k-il
Details Dat file Parser  
(goe06k-il) GOE 6K AIRFOIL
Gottingen 6K airfoil
Max thickness 7.5% at 50% chord.
Max camber 3.1% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 6K AIRFOIL
       16.       16.

 0.0000000 0.0000000
 0.0250000 0.0157100
 0.0500000 0.0234300
 0.0750000 0.0295400
 0.1000000 0.0349600
 0.1500000 0.0436900
 0.2000000 0.0506200
 0.3000000 0.0607800
 0.4000000 0.0665400
 0.5000000 0.0685000
 0.6000000 0.0668600
 0.7000000 0.0594200
 0.8000000 0.0467800
 0.9000000 0.0279400
 0.9500000 0.0162700
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0250000 -.0070900
 0.0500000 -.0079700
 0.0750000 -.0085500
 0.1000000 -.0088400
 0.1500000 -.0093100
 0.2000000 -.0090800
 0.3000000 -.0082200
 0.4000000 -.0073600
 0.5000000 -.0065000
 0.6000000 -.0056400
 0.7000000 -.0047800
 0.8000000 -.0039200
 0.9000000 -.0030600
 0.9500000 -.0026300
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for GOE 6K AIRFOIL (goe06k-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe06k-il50,000926.4 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe06k-il50,000528.3 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe06k-il100,000945.7 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe06k-il100,000544.6 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe06k-il200,000974.4 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe06k-il200,000577 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe06k-il500,0009117.9 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe06k-il500,0005116.5 at α=2.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe06k-il1,000,0009147.6 at α=1.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe06k-il1,000,0005132.8 at α=1.25°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
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