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GOE 599 AIRFOIL (goe599-il)

GOE 599 AIRFOIL - Gottingen 599 airfoil


Airfoil goe599-il
Details Dat file Parser  
(goe599-il) GOE 599 AIRFOIL
Gottingen 599 airfoil
Max thickness 10% at 29.6% chord.
Max camber 1.5% at 59.7% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 599 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0116500 0.0146800
 0.0237600 0.0213800
 0.0483200 0.0288100
 0.0729500 0.0352500
 0.0976300 0.0406900
 0.1471700 0.0485700
 0.1967700 0.0554600
 0.2963800 0.0622600
 0.3963000 0.0635800
 0.4964200 0.0614200
 0.5967500 0.0557600
 0.6972899 0.0466200
 0.7979900 0.0344800
 0.8987900 0.0208500
 0.9493100 0.0118000
 1.0000000 0.0017500

 0.0000000 0.0000000
 0.0132200 -.0122300
 0.0259900 -.0169900
 0.0513700 -.0235100
 0.0766400 -.0280400
 0.1017800 -.0305700
 0.1520500 -.0351400
 0.2021700 -.0372200
 0.3021800 -.0374000
 0.4020500 -.0350800
 0.5017900 -.0307700
 0.6014600 -.0249700
 0.7011200 -.0191600
 0.8007801 -.0133500
 0.9004400 -.0075500
 0.9502700 -.0046500
 1.0000000 -.0017500
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Lednicer format dat file
Selig format dat file

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Polars for GOE 599 AIRFOIL (goe599-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe599-il50,000934.2 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe599-il50,000533.1 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe599-il100,000948.5 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe599-il100,000544.1 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe599-il200,000961.5 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe599-il200,000551.2 at α=2.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe599-il500,000972.8 at α=2.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe599-il500,000565.5 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe599-il1,000,000979.8 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe599-il1,000,000580.2 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
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