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GOE 553 AIRFOIL (goe553-il)

GOE 553 AIRFOIL - Gottingen 553 airfoil


Airfoil goe553-il
Details Dat file Parser  
(goe553-il) GOE 553 AIRFOIL
Gottingen 553 airfoil
Max thickness 13.7% at 29.6% chord.
Max camber 4.7% at 39.6% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 553 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0115800 0.0288700
 0.0237000 0.0407600
 0.0481600 0.0575400
 0.0727300 0.0708300
 0.0973700 0.0821200
 0.1469100 0.0967000
 0.1965800 0.1067900
 0.2963400 0.1144800
 0.3964400 0.1111900
 0.4967900 0.1004000
 0.5973200 0.0836100
 0.6979100 0.0653300
 0.7985399 0.0455500
 0.8992400 0.0237800
 0.9496000 0.0123900
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0129500 -.0140900
 0.0255700 -.0176800
 0.0506700 -.0208800
 0.0757400 -.0230800
 0.1007600 -.0237800
 0.1507900 -.0246700
 0.2007900 -.0245700
 0.3007200 -.0223800
 0.4005700 -.0176800
 0.5003200 -.0099900
 0.6000600 -.0018000
 0.6998600 0.0044000
 0.7997700 0.0070900
 0.8998300 0.0052900
 0.9499100 0.0029000
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for GOE 553 AIRFOIL (goe553-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe553-il50,000911.2 at α=1°Mach=0 Ncrit=9Xfoil predictionDetails
   goe553-il50,000530.1 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe553-il100,000945.9 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe553-il100,000554.5 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe553-il200,000973 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   goe553-il200,000575 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe553-il500,0009105.5 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   goe553-il500,0005102.3 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe553-il1,000,0009130.5 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe553-il1,000,0005122.6 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
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