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CLARK X AIRFOIL (clarkx-il)

CLARK X AIRFOIL - CLARK X airfoil


Airfoil clarkx-il
Details Dat file Parser  
(clarkx-il) CLARK X AIRFOIL
CLARK X airfoil
Max thickness 11.7% at 30% chord.
Max camber 3.3% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
CLARK X AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125000 0.0186000
 0.0250000 0.0276000
 0.0500000 0.0416000
 0.0750000 0.0522000
 0.1000000 0.0608000
 0.1500000 0.0728000
 0.2000000 0.0808000
 0.3000000 0.0890000
 0.4000000 0.0900000
 0.5000000 0.0852000
 0.6000000 0.0755000
 0.7000000 0.0615000
 0.8000000 0.0442000
 0.9000000 0.0240000
 0.9500000 0.0129000
 1.0000000 0.0012000

 0.0000000 0.0000000
 0.0125000 -.0163000
 0.0250000 -.0220000
 0.0500000 -.0272000
 0.0750000 -.0296000
 0.1000000 -.0310000
 0.1500000 -.0318000
 0.2000000 -.0317000
 0.3000000 -.0280000
 0.4000000 -.0240000
 0.5000000 -.0200000
 0.6000000 -.0160000
 0.7000000 -.0120000
 0.8000000 -.0080000
 0.9000000 -.0040000
 0.9500000 -.0020000
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for CLARK X AIRFOIL (clarkx-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   clarkx-il50,000932.9 at α=9.75°Mach=0 Ncrit=9Xfoil predictionDetails
   clarkx-il50,000536.4 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   clarkx-il100,000954.2 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   clarkx-il100,000555.2 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   clarkx-il200,000976.2 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   clarkx-il200,000572.3 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   clarkx-il500,0009103.7 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   clarkx-il500,000592.8 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   clarkx-il1,000,0009122.4 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   clarkx-il1,000,0005107.9 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
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