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GOE 682 AIRFOIL (goe682-il)

GOE 682 AIRFOIL - Gottingen 682 airfoil


Airfoil goe682-il
Details Dat file Parser  
(goe682-il) GOE 682 AIRFOIL
Gottingen 682 airfoil
Max thickness 10.7% at 30% chord.
Max camber 4.3% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 682 AIRFOIL
       15.       15.

 0.0000000 0.0000000
 0.0125000 0.0208100
 0.0250000 0.0311200
 0.0500000 0.0462500
 0.0750000 0.0573800
 0.1000000 0.0665000
 0.2000000 0.0865000
 0.3000000 0.0945000
 0.4000000 0.0940000
 0.5000000 0.0880000
 0.6000000 0.0765000
 0.7000000 0.0615000
 0.8000000 0.0435000
 0.9000000 0.0230000
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0125000 -.0141900
 0.0250000 -.0183700
 0.0500000 -.0212500
 0.0750000 -.0221300
 0.1000000 -.0225000
 0.2000000 -.0180000
 0.3000000 -.0120000
 0.4000000 -.0075000
 0.5000000 -.0045000
 0.6000000 -.0015000
 0.7000000 0.0000000
 0.8000000 0.0010000
 0.9000000 0.0010000
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for GOE 682 AIRFOIL (goe682-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe682-il50,000925.4 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   goe682-il50,000537.5 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   goe682-il100,000955.9 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe682-il100,000557.4 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe682-il200,000978.7 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe682-il200,000575.3 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe682-il500,0009106.3 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe682-il500,000597.4 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe682-il1,000,0009126.5 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe682-il1,000,0005112.6 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
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