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GOE 574 AIRFOIL (goe574-il)

GOE 574 AIRFOIL - Gottingen 574 airfoil


Airfoil goe574-il
Details Dat file Parser  
(goe574-il) GOE 574 AIRFOIL
Gottingen 574 airfoil
Max thickness 10.3% at 30% chord.
Max camber 4.9% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 574 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0124200 0.0150600
 0.0248800 0.0241200
 0.0498100 0.0387500
 0.0747500 0.0508700
 0.0996900 0.0620000
 0.1496100 0.0777500
 0.1995600 0.0885000
 0.2995000 0.1005000
 0.3995100 0.0990000
 0.4995400 0.0915000
 0.5996000 0.0800000
 0.6996700 0.0655000
 0.7997600 0.0490000
 0.8998400 0.0315000
 0.9499000 0.0197500
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0125400 -.0079400
 0.0250400 -.0088700
 0.0500500 -.0097500
 0.0750500 -.0096200
 0.1000500 -.0090000
 0.1500300 -.0067500
 0.2000300 -.0050000
 0.3000100 -.0020000
 0.4000000 -.0005000
 0.5000000 0.0000000
 0.6000100 -.0010000
 0.7000100 -.0020000
 0.8000200 -.0035000
 0.9000200 -.0045000
 0.9500300 -.0027800
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for GOE 574 AIRFOIL (goe574-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe574-il50,000934.4 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe574-il50,000535.7 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe574-il100,000956 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe574-il100,000555.8 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe574-il200,000974.5 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe574-il200,000573.1 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe574-il500,0009100 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe574-il500,000597.3 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe574-il1,000,0009121.8 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe574-il1,000,0005118.1 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
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