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GOE 652 AIRFOIL (goe652-il)

GOE 652 AIRFOIL - Gottingen 652 airfoil


Airfoil goe652-il
Details Dat file Parser  
(goe652-il) GOE 652 AIRFOIL
Gottingen 652 airfoil
Max thickness 17.1% at 20% chord.
Max camber 9.3% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 652 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125000 0.0377300
 0.0250000 0.0534500
 0.0500000 0.0754000
 0.0750000 0.0913500
 0.1000000 0.1043000
 0.1500000 0.1227000
 0.2000000 0.1361000
 0.3000000 0.1479000
 0.4000000 0.1497000
 0.5000000 0.1415000
 0.6000000 0.1253000
 0.7000000 0.1016000
 0.8000000 0.0719000
 0.9000000 0.0387000
 0.9500000 0.0206000
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0125000 -.0302700
 0.0250000 -.0415500
 0.0500000 -.0501000
 0.0750000 -.0526500
 0.1000000 -.0522000
 0.1500000 -.0458000
 0.2000000 -.0344000
 0.3000000 -.0061000
 0.4000000 0.0222000
 0.5000000 0.0435000
 0.6000000 0.0563000
 0.7000000 0.0596000
 0.8000000 0.0514000
 0.9000000 0.0312000
 0.9500000 0.0166000
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for GOE 652 AIRFOIL (goe652-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe652-il50,00095.4 at α=10°Mach=0 Ncrit=9Xfoil predictionDetails
   goe652-il50,000521.2 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe652-il100,000949.6 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe652-il100,000553.1 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe652-il200,000977.3 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe652-il200,000578 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe652-il500,0009112.7 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe652-il500,0005102.8 at α=2.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe652-il1,000,0009135.7 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe652-il1,000,0005115.7 at α=0.5°Mach=0 Ncrit=5Xfoil predictionDetails
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