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GOE 504 AIRFOIL (goe504-il)

GOE 504 AIRFOIL - Gottingen 504 airfoil


Airfoil goe504-il
Details Dat file Parser  
(goe504-il) GOE 504 AIRFOIL
Gottingen 504 airfoil
Max thickness 18% at 29.2% chord.
Max camber 5.4% at 39.2% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 504 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0112300 0.0231200
 0.0229500 0.0372600
 0.0467000 0.0600700
 0.0706900 0.0783900
 0.0949000 0.0927200
 0.1437400 0.1139100
 0.1929800 0.1276100
 0.2922400 0.1410700
 0.3922200 0.1415700
 0.4927400 0.1321000
 0.5936700 0.1151500
 0.6949300 0.0922200
 0.7964100 0.0653000
 0.8981100 0.0344000
 0.9490500 0.0172000
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0132900 -.0142700
 0.0260500 -.0190700
 0.0515000 -.0271700
 0.0767800 -.0322800
 0.1019800 -.0358900
 0.1522600 -.0411300
 0.2023300 -.0423700
 0.3021100 -.0383800
 0.4018100 -.0329000
 0.5015100 -.0274200
 0.6012100 -.0219300
 0.7009100 -.0164500
 0.8006000 -.0109700
 0.9003000 -.0054800
 0.9501500 -.0027400
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for GOE 504 AIRFOIL (goe504-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe504-il50,00093.7 at α=9.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe504-il50,000513.7 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe504-il100,000934.2 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe504-il100,000543.6 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe504-il200,000966.2 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   goe504-il200,000562.8 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe504-il500,000991.7 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   goe504-il500,000585.1 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe504-il1,000,0009114.9 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe504-il1,000,0005104.1 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
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