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GOE 559 AIRFOIL (goe559-il)

GOE 559 AIRFOIL - Gottingen 559 airfoil


Airfoil goe559-il
Details Dat file Parser  
(goe559-il) GOE 559 AIRFOIL
Gottingen 559 airfoil
Max thickness 11.2% at 30% chord.
Max camber 3.4% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 559 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125000 0.0055000
 0.0250000 0.0115000
 0.0500000 0.0230000
 0.0750000 0.0340000
 0.1000000 0.0445000
 0.1500000 0.0625000
 0.2000000 0.0760000
 0.3000000 0.0900000
 0.4000000 0.0885000
 0.5000000 0.0790000
 0.6000000 0.0665000
 0.7000000 0.0515000
 0.8000000 0.0365000
 0.9000000 0.0190000
 0.9500000 0.0100000
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0125000 -.0015000
 0.0250000 -.0030000
 0.0500000 -.0060000
 0.0750000 -.0085000
 0.1000000 -.0110000
 0.1500000 -.0155000
 0.2000000 -.0185000
 0.3000000 -.0215000
 0.4000000 -.0210000
 0.5000000 -.0185000
 0.6000000 -.0155000
 0.7000000 -.0120000
 0.8000000 -.0085000
 0.9000000 -.0045000
 0.9500000 -.0025000
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for GOE 559 AIRFOIL (goe559-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe559-il50,000930.1 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   goe559-il50,000528.6 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe559-il100,000940.4 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe559-il100,000538.6 at α=2.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe559-il200,000950.2 at α=2°Mach=0 Ncrit=9Xfoil predictionDetails
   goe559-il200,000550 at α=1.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe559-il500,000966.3 at α=1.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe559-il500,000564.2 at α=1.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe559-il1,000,000976.8 at α=1.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe559-il1,000,000574.2 at α=1.5°Mach=0 Ncrit=5Xfoil predictionDetails
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