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GOE 600 AIRFOIL (goe600-il)

GOE 600 AIRFOIL - Gottingen 600 airfoil


Airfoil goe600-il
Details Dat file Parser  
(goe600-il) GOE 600 AIRFOIL
Gottingen 600 airfoil
Max thickness 13.1% at 29.4% chord.
Max camber 1.9% at 49.4% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 600 AIRFOIL
       17.       17.

 0.0000100 0.0000000
 0.0111200 0.0178600
 0.0229700 0.0262800
 0.0469800 0.0391400
 0.0712900 0.0480200
 0.0957100 0.0554200
 0.1448800 0.0662300
 0.1943100 0.0735600
 0.2937100 0.0812600
 0.3936100 0.0825000
 0.4938600 0.0792700
 0.5946100 0.0695800
 0.6957100 0.0554200
 0.7969600 0.0392600
 0.8983999 0.0206300
 0.9491000 0.0115600
 1.0000000 0.0025000

 0.0000100 0.0000000
 0.0137100 -.0154400
 0.0267100 -.0219300
 0.0523300 -.0299400
 0.0778000 -.0359700
 0.1030700 -.0395100
 0.1534300 -.0441100
 0.2037000 -.0477100
 0.3038400 -.0494500
 0.4036300 -.0467200
 0.5031800 -.0410000
 0.6025800 -.0333000
 0.7019899 -.0256000
 0.8013900 -.0178900
 0.9007900 -.0101900
 0.9504901 -.0063400
 1.0000000 -.0025000
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Lednicer format dat file
Selig format dat file

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Polars for GOE 600 AIRFOIL (goe600-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe600-il50,000932.5 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe600-il50,000533.9 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   goe600-il100,000951.1 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe600-il100,000549.4 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe600-il200,000969.6 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe600-il200,000562.9 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe600-il500,000991.2 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe600-il500,000576.8 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe600-il1,000,000999.6 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe600-il1,000,000586 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
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