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GOE 601 AIRFOIL (goe601-il)

GOE 601 AIRFOIL - Gottingen 601 airfoil


Airfoil goe601-il
Details Dat file Parser  
(goe601-il) GOE 601 AIRFOIL
Gottingen 601 airfoil
Max thickness 16% at 39% chord.
Max camber 2.5% at 49% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 601 AIRFOIL
       17.       17.

 0.0000200 0.0000000
 0.0103200 0.0220300
 0.0219100 0.0311900
 0.0454200 0.0460400
 0.0692300 0.0579200
 0.0932400 0.0678200
 0.1418000 0.0821800
 0.1909100 0.0910900
 0.2900700 0.0995000
 0.3897700 0.1024700
 0.4901100 0.0990100
 0.5911000 0.0891100
 0.6927300 0.0727700
 0.7948600 0.0514800
 0.8971800 0.0282200
 0.9486200 0.0138600
 1.0000000 0.0000000

 0.0000200 0.0000000
 0.0146300 -.0210400
 0.0278500 -.0282200
 0.0538400 -.0381200
 0.0794800 -.0445500
 0.1048700 -.0485100
 0.1555700 -.0554400
 0.2059600 -.0594000
 0.3060600 -.0603900
 0.4057100 -.0569300
 0.5048600 -.0485100
 0.6039700 -.0396000
 0.7029800 -.0297000
 0.8019900 -.0198000
 0.9009900 -.0099000
 0.9505000 -.0049500
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for GOE 601 AIRFOIL (goe601-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe601-il50,000925.2 at α=11.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe601-il50,000528 at α=9°Mach=0 Ncrit=5Xfoil predictionDetails
   goe601-il100,000947.7 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe601-il100,000544.1 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe601-il200,000969.9 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe601-il200,000557.4 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe601-il500,000982.8 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe601-il500,000569 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe601-il1,000,000991.2 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe601-il1,000,000582.4 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
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