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GOE 207 (AVIATIK V8) AIRFOIL (goe207-il)

GOE 207 (AVIATIK V8) AIRFOIL - Gottingen 207 (AVIATIK V8) airfoil


Airfoil goe207-il
Details Dat file Parser  
(goe207-il) GOE 207 (AVIATIK V8) AIRFOIL
Gottingen 207 (AVIATIK V8) airfoil
Max thickness 8.8% at 19.9% chord.
Max camber 6.6% at 29.9% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 207 (AVIATIK V8) AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0122500 0.0222400
 0.0246400 0.0329700
 0.0494000 0.0543500
 0.0742200 0.0702200
 0.0991000 0.0812000
 0.1489100 0.0986500
 0.1988200 0.1071000
 0.2987900 0.1098000
 0.3988600 0.1030100
 0.4990000 0.0902100
 0.5991700 0.0751200
 0.6993600 0.0578300
 0.7995600 0.0397400
 0.8997600 0.0215400
 0.9498600 0.0129000
 1.0000000 0.0037500

 0.0000000 0.0000000
 0.0126600 -.0146600
 0.0251500 -.0134200
 0.0500800 -.0071500
 0.0750000 0.0000300
 0.0999400 0.0053000
 0.1498500 0.0137600
 0.1997900 0.0194100
 0.2997500 0.0228100
 0.3997600 0.0216200
 0.4997900 0.0187200
 0.5998400 0.0145300
 0.6998800 0.0106300
 0.7999300 0.0060400
 0.8999900 0.0009400
 0.9500100 -.0011000
 1.0000000 -.0037500
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Lednicer format dat file
Selig format dat file

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Polars for GOE 207 (AVIATIK V8) AIRFOIL (goe207-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe207-il50,000920.8 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   goe207-il50,000533.9 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe207-il100,000947.4 at α=10.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe207-il100,000552 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   goe207-il200,000970.4 at α=9.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe207-il200,000571.6 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe207-il500,000999.1 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe207-il500,000596.9 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe207-il1,000,0009120.2 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe207-il1,000,0005113.9 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
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