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GOE 611 AIRFOIL (goe611-il)

GOE 611 AIRFOIL - Gottingen 611 airfoil


Airfoil goe611-il
Details Dat file Parser  
(goe611-il) GOE 611 AIRFOIL
Gottingen 611 airfoil
Max thickness 12.9% at 29.9% chord.
Max camber 5.8% at 39.9% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 611 AIRFOIL
       16.       16.

 0.0000000 0.0000000
 0.0123800 0.0250600
 0.0248100 0.0396200
 0.0497200 0.0597400
 0.0746500 0.0743500
 0.0996000 0.0839700
 0.1495200 0.1002100
 0.1994700 0.1114500
 0.2994200 0.1224200
 0.3994200 0.1224000
 0.4994600 0.1143700
 0.5995200 0.1008500
 0.6996100 0.0818200
 0.7997200 0.0583000
 0.8998400 0.0332700
 1.0000000 0.0032500

 0.0000000 0.0000000
 0.0125400 -.0074400
 0.0250400 -.0078800
 0.0500400 -.0077600
 0.0750400 -.0076400
 0.1000400 -.0075200
 0.1500300 -.0072900
 0.2000300 -.0070500
 0.3000300 -.0065700
 0.4000300 -.0061000
 0.5000300 -.0056200
 0.6000200 -.0051500
 0.7000200 -.0046700
 0.8000200 -.0042000
 0.9000200 -.0037200
 1.0000000 -.0032500
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Lednicer format dat file
Selig format dat file

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Polars for GOE 611 AIRFOIL (goe611-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe611-il50,000910 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe611-il50,000531.2 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe611-il100,000952.7 at α=9°Mach=0 Ncrit=9Xfoil predictionDetails
   goe611-il100,000556.4 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   goe611-il200,000977.3 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe611-il200,000575.8 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe611-il500,0009106.6 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe611-il500,000597 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe611-il1,000,0009125.6 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe611-il1,000,0005107.9 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
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