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GOE 591 AIRFOIL (goe591-il)

GOE 591 AIRFOIL - Gottingen 591 airfoil


Airfoil goe591-il
Details Dat file Parser  
(goe591-il) GOE 591 AIRFOIL
Gottingen 591 airfoil
Max thickness 11.2% at 30% chord.
Max camber 5.1% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 591 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125000 0.0217200
 0.0250000 0.0334400
 0.0500000 0.0498800
 0.0750000 0.0628100
 0.1000000 0.0722500
 0.1500000 0.0866300
 0.2000000 0.0960000
 0.3000000 0.1052500
 0.4000000 0.1045000
 0.5000000 0.0972500
 0.6000000 0.0850000
 0.7000000 0.0682500
 0.8000000 0.0480000
 0.9000000 0.0257500
 0.9500000 0.0131300
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0125000 -.0107800
 0.0250000 -.0135600
 0.0500000 -.0161200
 0.0750000 -.0161900
 0.1000000 -.0157500
 0.1500000 -.0138800
 0.2000000 -.0110000
 0.3000000 -.0067500
 0.4000000 -.0035000
 0.5000000 -.0012500
 0.6000000 -.0005000
 0.7000000 0.0002500
 0.8000000 0.0005000
 0.9000000 0.0002500
 0.9500000 0.0006300
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for GOE 591 AIRFOIL (goe591-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe591-il50,000916 at α=14.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe591-il50,000534.4 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe591-il100,000952.7 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe591-il100,000557.3 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe591-il200,000977.2 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe591-il200,000576.9 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   goe591-il500,0009108 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   goe591-il500,0005103.1 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe591-il1,000,0009132.3 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe591-il1,000,0005122.7 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
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