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GOE 621 AIRFOIL (goe621-il)

GOE 621 AIRFOIL - Gottingen 621 airfoil


Airfoil goe621-il
Details Dat file Parser  
(goe621-il) GOE 621 AIRFOIL
Gottingen 621 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 621 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
 0.9001200 -.0025400
 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 621 AIRFOIL (goe621-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe621-il50,00099.3 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe621-il50,000527.6 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe621-il100,000951.1 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe621-il100,000549.2 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe621-il200,000974.7 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe621-il200,000570.1 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe621-il500,0009105.5 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe621-il500,000584.2 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe621-il1,000,0009120.7 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   goe621-il1,000,000599.8 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
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