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GOE 612 AIRFOIL (goe612-il)

GOE 612 AIRFOIL - Gottingen 612 airfoil


Airfoil goe612-il
Details Dat file Parser  
(goe612-il) GOE 612 AIRFOIL
Gottingen 612 airfoil
Max thickness 15% at 29.5% chord.
Max camber 5% at 49.5% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 612 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0112900 0.0265100
 0.0231600 0.0405500
 0.0472200 0.0611500
 0.0715500 0.0757600
 0.0960700 0.0863700
 0.1453800 0.1016100
 0.1949300 0.1113700
 0.2945500 0.1199000
 0.3945000 0.1209500
 0.4947900 0.1145100
 0.5954500 0.1000900
 0.6963500 0.0801800
 0.7974200 0.0567800
 0.8987100 0.0283900
 0.9494000 0.0132000
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0134300 -.0203900
 0.0262000 -.0263100
 0.0514600 -.0321600
 0.0766200 -.0355100
 0.1016800 -.0368700
 0.1517100 -.0376000
 0.2016500 -.0363200
 0.3013600 -.0297900
 0.4009700 -.0212600
 0.5006200 -.0137200
 0.6004000 -.0086800
 0.7002600 -.0056400
 0.8001400 -.0030900
 0.9000700 -.0015500
 0.9500600 -.0012700
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for GOE 612 AIRFOIL (goe612-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe612-il50,00099.4 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe612-il50,000527.9 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe612-il100,000951.3 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe612-il100,000549.3 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe612-il200,000974.7 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe612-il200,000570.1 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe612-il500,0009105.5 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe612-il500,000585.1 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe612-il1,000,0009121.6 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   goe612-il1,000,0005100 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
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