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GOE 615 AIRFOIL (goe615-il)

GOE 615 AIRFOIL - Gottingen 615 airfoil


Airfoil goe615-il
Details Dat file Parser  
(goe615-il) GOE 615 AIRFOIL
Gottingen 615 airfoil
Max thickness 13.7% at 29.7% chord.
Max camber 5.6% at 39.7% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 615 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0117100 0.0298100
 0.0237800 0.0461300
 0.0483100 0.0637800
 0.0729300 0.0779300
 0.0976400 0.0890900
 0.1472300 0.1044000
 0.1969900 0.1137200
 0.2967700 0.1218600
 0.3967800 0.1215100
 0.4970400 0.1116700
 0.5974200 0.0973300
 0.6979300 0.0780000
 0.7985500 0.0546600
 0.8992400 0.0288300
 0.9496000 0.0151600
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0128900 -.0146600
 0.0255000 -.0188200
 0.0505600 -.0211600
 0.0756000 -.0225000
 0.1006100 -.0228300
 0.1506000 -.0225100
 0.2005400 -.0201900
 0.3003900 -.0145400
 0.4002500 -.0093900
 0.5001400 -.0052500
 0.6000600 -.0021000
 0.7000000 0.0000500
 0.7999900 0.0002000
 0.8999900 0.0003500
 0.9500000 0.0001700
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for GOE 615 AIRFOIL (goe615-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe615-il50,000910.3 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe615-il50,000530.5 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe615-il100,000951 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe615-il100,000553 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe615-il200,000974.6 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe615-il200,000572.2 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe615-il500,0009104.1 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe615-il500,000593.5 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe615-il1,000,0009125.5 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe615-il1,000,0005102.7 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
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