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GOE 522 AIRFOIL (goe522-il)

GOE 522 AIRFOIL - Gottingen 522 airfoil


Airfoil goe522-il
Details Dat file Parser  
(goe522-il) GOE 522 AIRFOIL
Gottingen 522 airfoil
Max thickness 21.8% at 28.6% chord.
Max camber 5.2% at 48.7% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 522 AIRFOIL
       17.       17.

 0.0000100 0.0000000
 0.0095100 0.0343300
 0.0206100 0.0503000
 0.0435100 0.0743100
 0.0669800 0.0918600
 0.0906600 0.1069300
 0.1386700 0.1296300
 0.1875100 0.1429000
 0.2863100 0.1565500
 0.3863800 0.1558000
 0.4873500 0.1446400
 0.5888000 0.1280200
 0.6908700 0.1044500
 0.7934500 0.0749300
 0.8965500 0.0394500
 0.9482500 0.0199700
 1.0000000 0.0000000

 0.0000100 0.0000000
 0.0151500 -.0301700
 0.0283000 -.0375200
 0.0543700 -.0497400
 0.0799600 -.0565000
 0.1053300 -.0607800
 0.1556900 -.0648800
 0.2058300 -.0664900
 0.3053300 -.0607800
 0.4044400 -.0506100
 0.5033700 -.0384600
 0.6023100 -.0263000
 0.7013700 -.0156300
 0.8006099 -.0069500
 0.9000700 -.0007400
 0.9499900 0.0001200
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for GOE 522 AIRFOIL (goe522-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe522-il50,00093 at α=10°Mach=0 Ncrit=9Xfoil predictionDetails
   goe522-il50,00059.8 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe522-il100,000932.1 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe522-il100,000537.6 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe522-il200,000957.1 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe522-il200,000551.6 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   goe522-il500,000973.7 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe522-il500,000563.5 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe522-il1,000,000989.4 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe522-il1,000,000570.7 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
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