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GOE 572 AIRFOIL (goe572-il)

GOE 572 AIRFOIL - Gottingen 572 airfoil


Airfoil goe572-il
Details Dat file Parser  
(goe572-il) GOE 572 AIRFOIL
Gottingen 572 airfoil
Max thickness 18.6% at 29.9% chord.
Max camber 8.3% at 29.9% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 572 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0122700 0.0310900
 0.0246300 0.0486800
 0.0494300 0.0763700
 0.0742600 0.0980600
 0.0991300 0.1162400
 0.1488900 0.1486200
 0.1987900 0.1659900
 0.2986800 0.1762400
 0.3987400 0.1684900
 0.4988800 0.1497400
 0.5990600 0.1254900
 0.6992600 0.0982400
 0.7994800 0.0690000
 0.8997600 0.0379800
 0.9498400 0.0216200
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0125700 -.0094100
 0.0250900 -.0123100
 0.0501100 -.0141200
 0.0751100 -.0144400
 0.1001100 -.0142500
 0.1501000 -.0133700
 0.2000900 -.0120000
 0.3000700 -.0097500
 0.4000600 -.0075000
 0.5000500 -.0062500
 0.6000500 -.0065000
 0.7000600 -.0077500
 0.8000700 -.0090000
 0.9000599 -.0082500
 0.9500600 -.0078700
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for GOE 572 AIRFOIL (goe572-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe572-il50,00093.1 at α=10.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe572-il50,000514.6 at α=1.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe572-il100,000929.9 at α=1.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe572-il100,000538.4 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
   goe572-il200,000955.7 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe572-il200,000554.8 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe572-il500,000979.9 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   goe572-il500,000577.5 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
   goe572-il1,000,0009103.8 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe572-il1,000,000598.6 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
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