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GOE 165 (MVA MK.11) AIRFOIL (goe165-il)

GOE 165 (MVA MK.11) AIRFOIL - Gottingen 165 (MVA MK.11) airfoil


Airfoil goe165-il
Details Dat file Parser  
(goe165-il) GOE 165 (MVA MK.11) AIRFOIL
Gottingen 165 (MVA MK.11) airfoil
Max thickness 12.1% at 19.7% chord.
Max camber 5.7% at 49.7% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 165 (MVA MK.11) AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0119500 0.0194400
 0.0240800 0.0324800
 0.0486500 0.0476800
 0.0732100 0.0628800
 0.0979300 0.0728800
 0.1475000 0.0881900
 0.1972300 0.0977000
 0.2970800 0.1029400
 0.3971300 0.1010800
 0.4973000 0.0952200
 0.5976600 0.0824700
 0.6980700 0.0678300
 0.7985300 0.0516800
 0.8991100 0.0313300
 0.9494600 0.0188600
 1.0000000 0.0006000

 0.0000000 0.0000000
 0.0126900 -.0066400
 0.0253100 -.0108800
 0.0504200 -.0148700
 0.0755500 -.0193500
 0.1006000 -.0209400
 0.1506900 -.0241200
 0.2006600 -.0233000
 0.3004200 -.0146700
 0.3999100 0.0032600
 0.4994300 0.0199800
 0.5992200 0.0274200
 0.6992400 0.0267600
 0.7993900 0.0215000
 0.8996400 0.0127500
 0.9498300 0.0060800
 1.0000000 -.0006000
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Lednicer format dat file
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Polars for GOE 165 (MVA MK.11) AIRFOIL (goe165-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe165-il50,000931.3 at α=10.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe165-il50,000539.9 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe165-il100,000954.4 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe165-il100,000553.4 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   goe165-il200,000969.3 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe165-il200,000566.6 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe165-il500,000985.7 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe165-il500,000579.1 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
   goe165-il1,000,000996.6 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe165-il1,000,000585.7 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
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