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GOE 802 A AIRFOIL (goe802a-il)

GOE 802 A AIRFOIL - Gottingen 802 A airfoil


Airfoil goe802a-il
Details Dat file Parser  
(goe802a-il) GOE 802 A AIRFOIL
Gottingen 802 A airfoil
Max thickness 9.8% at 30% chord.
Max camber 6.1% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 802 A AIRFOIL
       17.       25.

 0.0000000 0.0000000
 0.0125000 0.0261500
 0.0250000 0.0398000
 0.0500000 0.0566000
 0.0750000 0.0689000
 0.1000000 0.0782000
 0.1500000 0.0918000
 0.2000000 0.1014000
 0.3000000 0.1096000
 0.4000000 0.1088000
 0.5000000 0.1015000
 0.6000000 0.0897000
 0.7000000 0.0734000
 0.8000000 0.0526000
 0.9000000 0.0288000
 0.9500000 0.0164000
 1.0000000 0.0040000

 0.0000000 0.0000000
 0.0125000 -.0118500
 0.0250000 -.0120000
 0.0500000 -.0094000
 0.0750000 -.0027000
 0.0850000 0.0030000
 0.0900000 0.0115000
 0.0950000 0.0165000
 0.1000000 0.0180000
 0.1050000 0.0165000
 0.1100000 0.0110000
 0.1150000 0.0050000
 0.1200000 0.0020000
 0.1250000 0.0010000
 0.1500000 -.0002000
 0.2000000 0.0044000
 0.3000000 0.0116000
 0.4000000 0.0148000
 0.5000000 0.0150000
 0.6000000 0.0147000
 0.7000000 0.0124000
 0.8000000 0.0086000
 0.9000000 0.0038000
 0.9500000 0.0019000
 1.0000000 0.0000000
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Lednicer format dat file
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Polars for GOE 802 A AIRFOIL (goe802a-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe802a-il50,000927.5 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe802a-il50,000539.2 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe802a-il100,000952.6 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe802a-il100,000561 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe802a-il200,000973.9 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe802a-il200,0005149.1 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   goe802a-il500,0009101.7 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe802a-il500,000591 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe802a-il1,000,0009101.1 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe802a-il1,000,0005175 at α=9.75°Mach=0 Ncrit=5Xfoil predictionDetails
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