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GOE 506 AIRFOIL (goe506-il)

GOE 506 AIRFOIL - Gottingen 506 airfoil


Airfoil goe506-il
Details Dat file Parser  
(goe506-il) GOE 506 AIRFOIL
Gottingen 506 airfoil
Max thickness 16.5% at 29.3% chord.
Max camber 4.7% at 39.3% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 506 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0112200 0.0240900
 0.0230300 0.0372200
 0.0468800 0.0589800
 0.0710400 0.0747600
 0.0953100 0.0885500
 0.1444300 0.1051500
 0.1937600 0.1177700
 0.2932900 0.1265400
 0.3933000 0.1263400
 0.4936100 0.1206600
 0.5940700 0.1109900
 0.6951100 0.0923400
 0.7964399 0.0672100
 0.8981400 0.0351000
 0.9490300 0.0183000
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0131800 -.0128000
 0.0259400 -.0176300
 0.0513400 -.0252800
 0.0766400 -.0309400
 0.1018900 -.0356000
 0.1521700 -.0409300
 0.2021900 -.0412800
 0.3020200 -.0379900
 0.4017300 -.0327100
 0.5014500 -.0274200
 0.6011700 -.0221400
 0.7008899 -.0168500
 0.8006099 -.0115700
 0.9003299 -.0062800
 0.9501899 -.0036400
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for GOE 506 AIRFOIL (goe506-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe506-il50,000910.2 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe506-il50,000528 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe506-il100,000945.1 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe506-il100,000540.7 at α=8.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe506-il200,000958 at α=1.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe506-il200,000548.4 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe506-il500,000964.2 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   goe506-il500,000561.9 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   goe506-il1,000,000981.1 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe506-il1,000,000575.9 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
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