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GOE 567 AIRFOIL (goe567-il)

GOE 567 AIRFOIL - Gottingen 567 airfoil


Airfoil goe567-il
Details Dat file Parser  
(goe567-il) GOE 567 AIRFOIL
Gottingen 567 airfoil
Max thickness 14.8% at 29.5% chord.
Max camber 5.3% at 49.5% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 567 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0114200 0.0235300
 0.0233600 0.0355700
 0.0476500 0.0511900
 0.0720200 0.0648100
 0.0965800 0.0744400
 0.1458100 0.0912100
 0.1952400 0.1034800
 0.2945900 0.1175500
 0.3945000 0.1196500
 0.4948400 0.1122600
 0.5955000 0.0978900
 0.6964300 0.0775400
 0.7974800 0.0546800
 0.8986500 0.0293400
 0.9493000 0.0151700
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0133000 -.0173900
 0.0261400 -.0248000
 0.0514800 -.0321300
 0.0766100 -.0349800
 0.1016900 -.0368200
 0.1517500 -.0380200
 0.2016900 -.0367200
 0.3013600 -.0296400
 0.4008500 -.0185600
 0.5003000 -.0064900
 0.5998400 0.0035900
 0.6995800 0.0091800
 0.7995500 0.0097800
 0.8996800 0.0068900
 0.9497800 0.0046900
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for GOE 567 AIRFOIL (goe567-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe567-il50,00096.1 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe567-il50,000521.6 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   goe567-il100,000949.7 at α=10.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe567-il100,000556 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   goe567-il200,000981 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe567-il200,000579.8 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe567-il500,0009115.2 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe567-il500,000595.8 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe567-il1,000,0009132.1 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   goe567-il1,000,0005103.5 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
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