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GOE 598 AIRFOIL (goe598-il)

GOE 598 AIRFOIL - Gottingen 598 airfoil


Airfoil goe598-il
Details Dat file Parser  
(goe598-il) GOE 598 AIRFOIL
Gottingen 598 airfoil
Max thickness 6.5% at 39.8% chord.
Max camber 1% at 49.8% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 598 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0121700 0.0084800
 0.0244900 0.0129700
 0.0492500 0.0189500
 0.0740600 0.0239300
 0.0989200 0.0274100
 0.1487200 0.0323700
 0.1985600 0.0363400
 0.2984100 0.0402900
 0.3983500 0.0417300
 0.4984100 0.0401900
 0.5986300 0.0346500
 0.6988700 0.0276700
 0.7992300 0.0195700
 0.8995600 0.0110300
 0.9497600 0.0060200
 1.0000000 0.0010000

 0.0000000 0.0000000
 0.0128600 -.0089900
 0.0254700 -.0119900
 0.0506700 -.0170000
 0.0757500 -.0190100
 0.1008100 -.0205200
 0.1509100 -.0230400
 0.2009500 -.0240600
 0.3009700 -.0246100
 0.4009400 -.0236600
 0.5008200 -.0207200
 0.6006600 -.0167700
 0.7005100 -.0128300
 0.8003500 -.0088900
 0.9001999 -.0049400
 0.9501200 -.0029700
 1.0000000 -.0010000
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Lednicer format dat file
Selig format dat file

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Polars for GOE 598 AIRFOIL (goe598-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe598-il50,000931.7 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   goe598-il50,000530.5 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe598-il100,000943.1 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe598-il100,000540.4 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe598-il200,000954.8 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe598-il200,000548.6 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe598-il500,000966.9 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe598-il500,000554.6 at α=2°Mach=0 Ncrit=5Xfoil predictionDetails
   goe598-il1,000,000972.5 at α=2°Mach=0 Ncrit=9Xfoil predictionDetails
   goe598-il1,000,000560.8 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
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