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GOE 511 AIRFOIL (goe511-il)

GOE 511 AIRFOIL - Gottingen 511 airfoil


Airfoil goe511-il
Details Dat file Parser  
(goe511-il) GOE 511 AIRFOIL
Gottingen 511 airfoil
Max thickness 16.6% at 19.9% chord.
Max camber 8% at 29.8% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 511 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0121000 0.0426100
 0.0244200 0.0607300
 0.0491800 0.0864700
 0.0740000 0.1057000
 0.0988600 0.1199400
 0.1486700 0.1399100
 0.1985400 0.1533900
 0.2984600 0.1623400
 0.3985000 0.1577900
 0.4986300 0.1447400
 0.5987900 0.1276900
 0.6990000 0.1056400
 0.7992401 0.0795900
 0.8995900 0.0435500
 0.9497899 0.0225200
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0126200 -.0123800
 0.0251500 -.0157600
 0.0501700 -.0180200
 0.0751800 -.0192900
 0.1001800 -.0190500
 0.1501700 -.0175700
 0.2001200 -.0126000
 0.3000300 -.0026500
 0.3999900 0.0008000
 0.5000300 -.0032500
 0.6001100 -.0113000
 0.7001200 -.0128500
 0.8001200 -.0124000
 0.9000900 -.0089500
 0.9500500 -.0054700
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for GOE 511 AIRFOIL (goe511-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe511-il50,00093.7 at α=11.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe511-il50,000525.2 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe511-il100,000941.4 at α=2.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe511-il100,000541.7 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe511-il200,000957.6 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe511-il200,000553.2 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe511-il500,000971.8 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe511-il500,000567 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   goe511-il1,000,000987.3 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe511-il1,000,000580.9 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
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