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GOE 199 (L.F.G. 5406) AIRFOIL (goe199-il)

GOE 199 (L.F.G. 5406) AIRFOIL - Gottingen 199 (L.F.G. 5406) airfoil


Airfoil goe199-il
Details Dat file Parser  
(goe199-il) GOE 199 (L.F.G. 5406) AIRFOIL
Gottingen 199 (L.F.G. 5406) airfoil
Max thickness 7.3% at 30% chord.
Max camber 5.2% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 199 (L.F.G. 5406) AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0124400 0.0206400
 0.0249100 0.0296700
 0.0498700 0.0444400
 0.0748400 0.0556200
 0.0998100 0.0656900
 0.1497800 0.0774300
 0.1997600 0.0833800
 0.2997400 0.0884700
 0.3997500 0.0876600
 0.4997600 0.0816500
 0.5997900 0.0724400
 0.6998300 0.0585300
 0.7998800 0.0419200
 0.8999299 0.0242100
 0.9499600 0.0149500
 1.0000000 0.0055000

 0.0000000 0.0000000
 0.0125200 -.0083600
 0.0250200 -.0067300
 0.0500100 -.0029500
 0.0750000 0.0008200
 0.0999900 0.0033900
 0.1499800 0.0081300
 0.1999700 0.0116800
 0.2999600 0.0151700
 0.3999600 0.0154600
 0.4999600 0.0141500
 0.5999700 0.0103400
 0.6999800 0.0052300
 0.8000000 0.0002200
 0.9000100 -.0031900
 0.9500200 -.0056400
 1.0000000 -.0055000
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Lednicer format dat file
Selig format dat file

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Polars for GOE 199 (L.F.G. 5406) AIRFOIL (goe199-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe199-il50,000936.8 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe199-il50,000540.4 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe199-il100,000955.7 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe199-il100,000554.9 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   goe199-il200,000972 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe199-il200,000567.6 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe199-il500,000989.8 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe199-il500,000589.5 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   goe199-il1,000,0009108.2 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe199-il1,000,0005106.3 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
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