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GOE 681 AIRFOIL (goe681-il)

GOE 681 AIRFOIL - Gottingen 681 airfoil


Airfoil goe681-il
Details Dat file Parser  
(goe681-il) GOE 681 AIRFOIL
Gottingen 681 airfoil
Max thickness 16.8% at 29.2% chord.
Max camber 4.4% at 39.2% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 681 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0106200 0.0301600
 0.0223200 0.0428900
 0.0460100 0.0638800
 0.0700400 0.0793800
 0.0942600 0.0918900
 0.1431600 0.1094500
 0.1925600 0.1190300
 0.2921400 0.1257600
 0.3922500 0.1240200
 0.4928300 0.1148000
 0.5938100 0.0991100
 0.6951000 0.0784400
 0.7966101 0.0542900
 0.8982100 0.0286400
 0.9490700 0.0148200
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0140700 -.0251200
 0.0269600 -.0313200
 0.0524600 -.0392200
 0.0777300 -.0436400
 0.1029100 -.0465700
 0.1530600 -.0489300
 0.2029600 -.0473200
 0.3026300 -.0420900
 0.4022700 -.0363600
 0.5018900 -.0301300
 0.6015300 -.0244000
 0.7011700 -.0186800
 0.8007801 -.0124500
 0.9003900 -.0062300
 0.9501899 -.0031100
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for GOE 681 AIRFOIL (goe681-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe681-il50,00099.7 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe681-il50,000526.5 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe681-il100,000944.3 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe681-il100,000542.2 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe681-il200,000961.7 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe681-il200,000555.4 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe681-il500,000979.3 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe681-il500,000573.9 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe681-il1,000,000997.8 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe681-il1,000,000594 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
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