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GOE 233 (MVA CA4) AIRFOIL (goe233-il)

GOE 233 (MVA CA4) AIRFOIL - Gottingen 233 (MVA CA4) airfoil


Airfoil goe233-il
Details Dat file Parser  
(goe233-il) GOE 233 (MVA CA4) AIRFOIL
Gottingen 233 (MVA CA4) airfoil
Max thickness 11.6% at 19.8% chord.
Max camber 8.2% at 49.8% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 233 (MVA CA4) AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0119300 0.0265600
 0.0242000 0.0371200
 0.0488500 0.0531600
 0.0735700 0.0659900
 0.0983400 0.0768300
 0.1479900 0.0929000
 0.1977600 0.1032800
 0.2974700 0.1167400
 0.3974100 0.1194000
 0.4975300 0.1138700
 0.5978200 0.1005400
 0.6982200 0.0821200
 0.7987300 0.0584900
 0.8993200 0.0313700
 0.9496400 0.0164600
 1.0000000 0.0015500

 0.0000000 0.0000000
 0.0127600 -.0121200
 0.0253200 -.0149500
 0.0504200 -.0195100
 0.0754500 -.0205700
 0.1004600 -.0210300
 0.1503900 -.0178400
 0.2002700 -.0126600
 0.2998500 0.0069900
 0.3992800 0.0333400
 0.4989100 0.0505000
 0.5987700 0.0567600
 0.6988300 0.0538300
 0.7991200 0.0405000
 0.8995600 0.0204800
 0.9498000 0.0092600
 1.0000000 -.0015500
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Lednicer format dat file
Selig format dat file

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Polars for GOE 233 (MVA CA4) AIRFOIL (goe233-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe233-il50,000926.4 at α=11.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe233-il50,000533.4 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   goe233-il100,000960.9 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe233-il100,000563.1 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe233-il200,000986.7 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   goe233-il200,000587.1 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe233-il500,0009120.7 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe233-il500,0005115.8 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   goe233-il1,000,0009146.8 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe233-il1,000,0005134.9 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
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