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GOE 562 AIRFOIL (goe562-il)

GOE 562 AIRFOIL - Gottingen 562 airfoil


Airfoil goe562-il
Details Dat file Parser  
(goe562-il) GOE 562 AIRFOIL
Gottingen 562 airfoil
Max thickness 14.1% at 30% chord.
Max camber 6.3% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 562 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0124100 0.0245400
 0.0248700 0.0375900
 0.0498000 0.0566700
 0.0747400 0.0732600
 0.0996900 0.0873500
 0.1496100 0.1100200
 0.1995700 0.1222000
 0.2995300 0.1330500
 0.3995500 0.1299000
 0.4995900 0.1172500
 0.5996500 0.0991000
 0.6997200 0.0789500
 0.7998000 0.0568000
 0.8998800 0.0336500
 0.9499300 0.0208200
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0125400 -.0104600
 0.0250400 -.0124100
 0.0500400 -.0123200
 0.0750400 -.0122400
 0.1000400 -.0121500
 0.1500400 -.0109700
 0.2000400 -.0103000
 0.3000300 -.0079500
 0.4000200 -.0066000
 0.5000200 -.0062500
 0.6000200 -.0059000
 0.7000200 -.0060500
 0.8000200 -.0067000
 0.9000300 -.0073500
 0.9500300 -.0061700
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for GOE 562 AIRFOIL (goe562-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe562-il50,00099.2 at α=-4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe562-il50,000525.8 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe562-il100,000940.9 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe562-il100,000550 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   goe562-il200,000970.4 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe562-il200,000570.6 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   goe562-il500,0009101.4 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe562-il500,000596.7 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe562-il1,000,0009126.3 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe562-il1,000,0005115.9 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
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