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EPPLER 664 AIRFOIL (e664-il)

EPPLER 664 AIRFOIL - Eppler E664 variable geometry sailplane airfoil


Airfoil e664-il
Details Dat file Parser  
(e664-il) EPPLER 664 AIRFOIL
Eppler E664 variable geometry sailplane airfoil
Max thickness 16.6% at 45.6% chord.
Max camber 2.6% at 40.7% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 EPPLER 664 AIRFOIL
      32.0      30.0
 
 0.0002300 0.0022900
 0.0046800 0.0115500
 0.0137100 0.0218300
 0.0271400 0.0326100
 0.0448700 0.0434800
 0.0667400 0.0541600
 0.0925800 0.0644100
 0.1221600 0.0740100
 0.1552100 0.0827700
 0.1914500 0.0905500
 0.2305100 0.0972000
 0.2720500 0.1026200
 0.3156400 0.1067000
 0.3608700 0.1093800
 0.4072700 0.1106000
 0.4563700 0.1102900
 0.5016700 0.1084000
 0.5486900 0.1048200
 0.5949700 0.0993700
 0.6404300 0.0916700
 0.6854900 0.0819700
 0.7300800 0.0712200
 0.7735300 0.0602000
 0.8151200 0.0494200
 0.8540700 0.0392700
 0.8896400 0.0300500
 0.9211000 0.0219300
 0.9477400 0.0149100
 0.9692300 0.0088100
 0.9855700 0.0039100
 0.9962300 0.0009200
 1.0000000 0.0000000
 
 0.0002300 0.0022900
 0.0014600 -.0052100
 0.0090300 -.0117300
 0.0223400 -.0181700
 0.0409700 -.0242300
 0.0647100 -.0297900
 0.0933400 -.0348200
 0.1265100 -.0393600
 0.1638000 -.0434100
 0.2047400 -.0469300
 0.2488200 -.0499000
 0.2955200 -.0522900
 0.3442900 -.0540600
 0.3945200 -.0552200
 0.4455600 -.0557200
 0.4967800 -.0554600
 0.5475400 -.0543300
 0.5971900 -.0521900
 0.6451200 -.0486700
 0.6911700 -.0432200
 0.7356100 -.0356700
 0.7790900 -.0262300
 0.8221900 -.0163700
 0.8639900 -.0080800
 0.9026000 -.0022400
 0.9364100 0.0010200
 0.9638500 0.0019800
 0.9840000 0.0014200
 0.9960200 0.0004500
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for EPPLER 664 AIRFOIL (e664-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   e664-il50,000919.3 at α=12°Mach=0 Ncrit=9Xfoil predictionDetails
   e664-il50,000519.7 at α=12°Mach=0 Ncrit=5Xfoil predictionDetails
   e664-il100,000939.9 at α=10°Mach=0 Ncrit=9Xfoil predictionDetails
   e664-il100,000533.2 at α=9.75°Mach=0 Ncrit=5Xfoil predictionDetails
   e664-il200,000957.6 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   e664-il200,000558.3 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   e664-il500,000990.8 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   e664-il500,000590.9 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   e664-il1,000,0009120.9 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   e664-il1,000,0005111.2 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
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