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GOE 561 AIRFOIL (goe561-il)

GOE 561 AIRFOIL - Gottingen 561 airfoil


Airfoil goe561-il
Details Dat file Parser  
(goe561-il) GOE 561 AIRFOIL
Gottingen 561 airfoil
Max thickness 25% at 29.8% chord.
Max camber 10.2% at 29.8% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 561 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0120500 0.0501100
 0.0243300 0.0742200
 0.0490000 0.1110400
 0.0737500 0.1391600
 0.0985700 0.1588900
 0.1482800 0.1913300
 0.1980900 0.2117800
 0.2979600 0.2271800
 0.3980100 0.2215800
 0.4982000 0.1994800
 0.5984700 0.1698900
 0.6987000 0.1334200
 0.7991500 0.0946900
 0.8993599 0.0520000
 0.9497300 0.0300500
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0126900 -.0213900
 0.0252200 -.0242700
 0.0502200 -.0240500
 0.0752100 -.0238200
 0.1002100 -.0236000
 0.1502100 -.0231500
 0.2002100 -.0232000
 0.3002000 -.0223000
 0.4001900 -.0214000
 0.5001800 -.0205000
 0.6001800 -.0196000
 0.7001500 -.0172000
 0.8001300 -.0148000
 0.9001100 -.0124000
 0.9500901 -.0104500
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for GOE 561 AIRFOIL (goe561-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe561-il50,00093.3 at α=-13.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe561-il50,00055.7 at α=-8.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe561-il100,00098.4 at α=-8°Mach=0 Ncrit=9Xfoil predictionDetails
   goe561-il100,00058.6 at α=-6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe561-il200,000928.7 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe561-il200,000520.9 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   goe561-il500,000943.2 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   goe561-il500,000533 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe561-il1,000,000949.1 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe561-il1,000,000542 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
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