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GOE 255 (MVA CA.6) AIRFOIL (goe255-il)

GOE 255 (MVA CA.6) AIRFOIL - Gottingen 255 (MVA CA.6) airfoil


Airfoil goe255-il
Details Dat file Parser  
(goe255-il) GOE 255 (MVA CA.6) AIRFOIL
Gottingen 255 (MVA CA.6) airfoil
Max thickness 18.5% at 29.1% chord.
Max camber 4.8% at 49.1% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 255 (MVA CA.6) AIRFOIL
       17.       17.

 0.0000100 0.0000000
 0.0108500 0.0239500
 0.0223200 0.0387500
 0.0457500 0.0613700
 0.0696700 0.0770300
 0.0937900 0.0897000
 0.1425200 0.1080800
 0.1915900 0.1214800
 0.2906900 0.1343400
 0.3903900 0.1387500
 0.4909900 0.1300200
 0.5920900 0.1142300
 0.6936901 0.0910700
 0.7955101 0.0648300
 0.8974800 0.0364000
 0.9486901 0.0189400
 1.0000000 0.0025000

 0.0000100 0.0000000
 0.0135200 -.0146600
 0.0265400 -.0221600
 0.0522400 -.0321800
 0.0776900 -.0387200
 0.1030300 -.0436600
 0.1534300 -.0493700
 0.2035900 -.0516900
 0.3035200 -.0507700
 0.4028700 -.0413800
 0.5022200 -.0320000
 0.6016200 -.0233100
 0.7010900 -.0157100
 0.8006800 -.0098100
 0.9004100 -.0059000
 0.9502700 -.0039500
 1.0000000 -.0025000
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Lednicer format dat file
Selig format dat file

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Polars for GOE 255 (MVA CA.6) AIRFOIL (goe255-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe255-il50,00095.1 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe255-il50,000515.2 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe255-il100,000941.4 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   goe255-il100,000547.3 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe255-il200,000972.4 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe255-il200,000571.1 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe255-il500,0009105.1 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe255-il500,000590.5 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe255-il1,000,0009127.2 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe255-il1,000,000596.8 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
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