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GOE 566 AIRFOIL (goe566-il)

GOE 566 AIRFOIL - Gottingen 566 airfoil


Airfoil goe566-il
Details Dat file Parser  
(goe566-il) GOE 566 AIRFOIL
Gottingen 566 airfoil
Max thickness 8.7% at 30% chord.
Max camber 2.6% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 566 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125000 0.0175000
 0.0250000 0.0250000
 0.0500000 0.0365000
 0.0750000 0.0440000
 0.1000000 0.0505000
 0.1500000 0.0595000
 0.2000000 0.0640000
 0.3000000 0.0685000
 0.4000000 0.0685000
 0.5000000 0.0650000
 0.6000000 0.0570000
 0.7000000 0.0460000
 0.8000000 0.0320000
 0.9000000 0.0160000
 0.9500000 0.0080000
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0125000 -.0115000
 0.0250000 -.0145000
 0.0500000 -.0170000
 0.0750000 -.0185000
 0.1000000 -.0190000
 0.1500000 -.0190000
 0.2000000 -.0185000
 0.3000000 -.0180000
 0.4000000 -.0175000
 0.5000000 -.0160000
 0.6000000 -.0135000
 0.7000000 -.0100000
 0.8000000 -.0065000
 0.9000000 -.0035000
 0.9500000 -.0020000
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for GOE 566 AIRFOIL (goe566-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe566-il50,000934.4 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe566-il50,000536.5 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe566-il100,000952.4 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe566-il100,000550.3 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   goe566-il200,000970 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe566-il200,000561.7 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe566-il500,000988.5 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe566-il500,000579.3 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe566-il1,000,000997.8 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe566-il1,000,000590 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
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