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GOE 619 AIRFOIL (goe619-il)

GOE 619 AIRFOIL - Gottingen 619 airfoil


Airfoil goe619-il
Details Dat file Parser  
(goe619-il) GOE 619 AIRFOIL
Gottingen 619 airfoil
Max thickness 13.7% at 19.5% chord.
Max camber 4.5% at 49.5% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 619 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0114900 0.0225200
 0.0233100 0.0375500
 0.0475400 0.0546400
 0.0719500 0.0677400
 0.0964800 0.0783400
 0.1458100 0.0930600
 0.1954400 0.1012900
 0.2951100 0.1087800
 0.3951100 0.1087800
 0.4954000 0.1022900
 0.5959800 0.0893200
 0.6967700 0.0718500
 0.7977101 0.0509000
 0.8987700 0.0274400
 0.9493400 0.0147200
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0133700 -.0194000
 0.0261400 -.0253200
 0.0514700 -.0326800
 0.0766200 -.0360500
 0.1016900 -.0374200
 0.1517200 -.0381700
 0.2016200 -.0359300
 0.3012400 -.0274400
 0.4008300 -.0184600
 0.5004900 -.0109800
 0.6003100 -.0069900
 0.7001600 -.0034900
 0.8000500 -.0010000
 0.9000000 0.0000000
 0.9499900 0.0002500
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for GOE 619 AIRFOIL (goe619-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe619-il50,000922 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe619-il50,000533.3 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe619-il100,000952.4 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe619-il100,000551.3 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe619-il200,000973.7 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe619-il200,000567.6 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe619-il500,000999.7 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   goe619-il500,000582 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe619-il1,000,0009108.9 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe619-il1,000,000599.6 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
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