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GOE 550 AIRFOIL (goe550-il)

GOE 550 AIRFOIL - Gottingen 550 airfoil


Airfoil goe550-il
Details Dat file Parser  
(goe550-il) GOE 550 AIRFOIL
Gottingen 550 airfoil
Max thickness 13% at 20% chord.
Max camber 4.3% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 550 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125000 0.0221100
 0.0250000 0.0322300
 0.0500000 0.0469500
 0.0750000 0.0581800
 0.1000000 0.0669000
 0.1500000 0.0813500
 0.2000000 0.0913000
 0.3000000 0.1002000
 0.4000000 0.1006000
 0.5000000 0.0940000
 0.6000000 0.0824000
 0.7000000 0.0663000
 0.8000000 0.0472000
 0.9000000 0.0261000
 0.9500000 0.0140500
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0125000 -.0178900
 0.0250000 -.0252700
 0.0500000 -.0335500
 0.0750000 -.0383200
 0.1000000 -.0406000
 0.1500000 -.0416500
 0.2000000 -.0382000
 0.3000000 -.0268000
 0.4000000 -.0174000
 0.5000000 -.0085000
 0.6000000 -.0031000
 0.7000000 0.0013000
 0.8000000 0.0027000
 0.9000000 0.0021000
 0.9500000 0.0015500
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for GOE 550 AIRFOIL (goe550-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe550-il50,000927.6 at α=11.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe550-il50,000533.7 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe550-il100,000953.1 at α=9°Mach=0 Ncrit=9Xfoil predictionDetails
   goe550-il100,000556.3 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe550-il200,000976.3 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   goe550-il200,000575.3 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe550-il500,0009106.3 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe550-il500,000598.4 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe550-il1,000,0009127.5 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe550-il1,000,0005114.8 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
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