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GOE 508 AIRFOIL (goe508-il)

GOE 508 AIRFOIL - Gottingen 508 airfoil


Airfoil goe508-il
Details Dat file Parser  
(goe508-il) GOE 508 AIRFOIL
Gottingen 508 airfoil
Max thickness 16.5% at 30% chord.
Max camber 5.6% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 508 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125000 0.0310100
 0.0250000 0.0475300
 0.0500000 0.0680500
 0.0750000 0.0840800
 0.1000000 0.0961000
 0.1500000 0.1136500
 0.2000000 0.1242000
 0.3000000 0.1363000
 0.4000000 0.1374000
 0.5000000 0.1275000
 0.6000000 0.1101000
 0.7000000 0.0862000
 0.8000000 0.0583000
 0.9000000 0.0294000
 0.9500000 0.0144500
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0125000 -.0209900
 0.0250000 -.0269700
 0.0500000 -.0319500
 0.0750000 -.0344300
 0.1000000 -.0349000
 0.1500000 -.0343500
 0.2000000 -.0328000
 0.3000000 -.0287000
 0.4000000 -.0246000
 0.5000000 -.0205000
 0.6000000 -.0164000
 0.7000000 -.0123000
 0.8000000 -.0082000
 0.9000000 -.0041000
 0.9500000 -.0020500
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for GOE 508 AIRFOIL (goe508-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe508-il50,00095.2 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe508-il50,000513.5 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe508-il100,000940.3 at α=9.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe508-il100,000543.7 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe508-il200,000971.3 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe508-il200,000569.6 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe508-il500,0009105.7 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe508-il500,000597.8 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe508-il1,000,0009132.8 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe508-il1,000,0005115.9 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
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