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GOE 620 AIRFOIL (goe620-il)

GOE 620 AIRFOIL - Gottingen 620 airfoil


Airfoil goe620-il
Details Dat file Parser  
(goe620-il) GOE 620 AIRFOIL
Gottingen 620 airfoil
Max thickness 17.5% at 30% chord.
Max camber 5.9% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 620 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125000 0.0321400
 0.0250000 0.0482900
 0.0500000 0.0700800
 0.0750000 0.0858600
 0.1000000 0.0971500
 0.1500000 0.1162300
 0.2000000 0.1283000
 0.3000000 0.1409500
 0.4000000 0.1421000
 0.5000000 0.1342500
 0.6000000 0.1189000
 0.7000000 0.0955500
 0.8000000 0.0677000
 0.9000000 0.0358500
 0.9500000 0.0184200
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0125000 -.0208600
 0.0250000 -.0282100
 0.0500000 -.0349300
 0.0750000 -.0391400
 0.1000000 -.0413500
 0.1500000 -.0427800
 0.2000000 -.0412000
 0.3000000 -.0340500
 0.4000000 -.0249000
 0.5000000 -.0162500
 0.6000000 -.0086000
 0.7000000 -.0034500
 0.8000000 -.0008000
 0.9000000 -.0006500
 0.9500000 -.0005800
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for GOE 620 AIRFOIL (goe620-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe620-il50,00094.2 at α=10°Mach=0 Ncrit=9Xfoil predictionDetails
   goe620-il50,000514.3 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe620-il100,000942.4 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe620-il100,000543.1 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe620-il200,000971.1 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe620-il200,000564.7 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   goe620-il500,000997.7 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   goe620-il500,000582.5 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe620-il1,000,0009117.6 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe620-il1,000,000587.6 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
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