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GOE 509 AIRFOIL (goe509-il)

GOE 509 AIRFOIL - Gottingen 509 airfoil


Airfoil goe509-il
Details Dat file Parser  
(goe509-il) GOE 509 AIRFOIL
Gottingen 509 airfoil
Max thickness 11.1% at 29.9% chord.
Max camber 5.2% at 39.9% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 509 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0123700 0.0260600
 0.0248200 0.0361200
 0.0497300 0.0542500
 0.0746700 0.0668700
 0.0996100 0.0775000
 0.1495500 0.0907500
 0.1995000 0.0995000
 0.2994700 0.1070000
 0.3994800 0.1035000
 0.4995200 0.0970000
 0.5995800 0.0850000
 0.6996601 0.0685000
 0.7997500 0.0495000
 0.8998600 0.0280000
 0.9499400 0.0132500
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0125400 -.0089400
 0.0250600 -.0118700
 0.0500700 -.0137500
 0.0750700 -.0141200
 0.1000700 -.0140000
 0.1500700 -.0132500
 0.2000600 -.0110000
 0.3000200 -.0035000
 0.4000000 0.0000000
 0.5000100 -.0025000
 0.6000400 -.0080000
 0.7000600 -.0110000
 0.8000500 -.0105000
 0.9000400 -.0080000
 0.9500300 -.0057500
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for GOE 509 AIRFOIL (goe509-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe509-il50,000919.8 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe509-il50,000535.3 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   goe509-il100,000951.6 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe509-il100,000552.2 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   goe509-il200,000969.3 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe509-il200,000568.8 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe509-il500,000996.7 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe509-il500,000591.1 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe509-il1,000,0009117.2 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe509-il1,000,000597.2 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
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