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BOEING 103 AIRFOIL (boe103-il)

BOEING 103 AIRFOIL - Boeing 103 airfoil


Airfoil boe103-il
Details Dat file Parser  
(boe103-il) BOEING 103 AIRFOIL
Boeing 103 airfoil
Max thickness 12.7% at 30% chord.
Max camber 3.6% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
BOEING 103 AIRFOIL
       18.       17.

 0.0000000 0.0000000
 0.0125000 0.0265900
 0.0187500 0.0345800
 0.0250000 0.0397700
 0.0500000 0.0555000
 0.0750000 0.0653000
 0.1000000 0.0730000
 0.1500000 0.0845000
 0.2000000 0.0920000
 0.3000000 0.0984800
 0.4000000 0.0984400
 0.5000000 0.0922000
 0.6000000 0.0809600
 0.7000000 0.0661200
 0.8000000 0.0476800
 0.9000000 0.0266400
 0.9500000 0.0151200
 1.0000000 0.0012000

 0.0000000 0.0000000
 0.0125000 -.0130000
 0.0250000 -.0169600
 0.0500000 -.0223200
 0.0750000 -.0255000
 0.1000000 -.0272400
 0.1500000 -.0285600
 0.2000000 -.0288800
 0.3000000 -.0287200
 0.4000000 -.0265000
 0.5000000 -.0228000
 0.6000000 -.0184400
 0.7000000 -.0134800
 0.8000000 -.0089200
 0.9000000 -.0043600
 0.9500000 -.0020800
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for BOEING 103 AIRFOIL (boe103-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   boe103-il50,000932.6 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   boe103-il50,000535 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   boe103-il100,000953.1 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   boe103-il100,000552.1 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   boe103-il200,000972 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   boe103-il200,000566.6 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   boe103-il500,000994.6 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   boe103-il500,000581.1 at α=2.5°Mach=0 Ncrit=5Xfoil predictionDetails
   boe103-il1,000,0009107.9 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   boe103-il1,000,000589 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
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