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GOE 416A AIRFOIL (goe416a-il)

GOE 416A AIRFOIL - Gottingen 416A airfoil


Airfoil goe416a-il
Details Dat file Parser  
(goe416a-il) GOE 416A AIRFOIL
Gottingen 416A airfoil
Max thickness 11.7% at 29.5% chord.
Max camber 1.3% at 59.6% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 416A AIRFOIL
       17.       17.

 0.0000100 0.0000000
 0.0113200 0.0155600
 0.0232400 0.0231700
 0.0474500 0.0336100
 0.0718500 0.0414700
 0.0963900 0.0474400
 0.1457000 0.0565900
 0.1953300 0.0614700
 0.2949100 0.0668600
 0.3950600 0.0648800
 0.4954600 0.0597300
 0.5961300 0.0508900
 0.6969000 0.0407700
 0.7978100 0.0287500
 0.8988600 0.0150500
 0.9493800 0.0081900
 1.0000000 0.0013500

 0.0000100 0.0000000
 0.0131300 -.0081000
 0.0260000 -.0130200
 0.0516300 -.0212700
 0.0771300 -.0278300
 0.1025400 -.0331900
 0.1531500 -.0413400
 0.2035100 -.0460000
 0.3038200 -.0500600
 0.4035700 -.0467700
 0.5027100 -.0355200
 0.6018100 -.0236700
 0.7011100 -.0145100
 0.8006099 -.0079300
 0.9002800 -.0036400
 0.9501899 -.0024400
 1.0000000 -.0013500
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Lednicer format dat file
Selig format dat file

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Polars for GOE 416A AIRFOIL (goe416a-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe416a-il50,000931.1 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe416a-il50,000534 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe416a-il100,000946.5 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe416a-il100,000547.3 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe416a-il200,000961.4 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe416a-il200,000557.7 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe416a-il500,000971 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   goe416a-il500,000567.5 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe416a-il1,000,000980.2 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe416a-il1,000,000575.4 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
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