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BOEING 106 AIRFOIL (boe106-il)

BOEING 106 AIRFOIL - Boeing 106 airfoil


Airfoil boe106-il
Details Dat file Parser  
(boe106-il) BOEING 106 AIRFOIL
Boeing 106 airfoil
Max thickness 13.1% 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
BOEING 106 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0100000 0.0213800
 0.0250000 0.0348000
 0.0500000 0.0490000
 0.0750000 0.0594000
 0.1000000 0.0676000
 0.1500000 0.0801500
 0.2000000 0.0895600
 0.3000000 0.0979400
 0.4000000 0.0975200
 0.5000000 0.0905000
 0.6000000 0.0788800
 0.7000000 0.0628600
 0.8000000 0.0436400
 0.9000000 0.0224200
 0.9500000 0.0114100
 1.0000000 0.0004000

 0.0000000 0.0000000
 0.0125000 -.0141000
 0.0250000 -.0191000
 0.0500000 -.0243000
 0.0750000 -.0277000
 0.1000000 -.0296000
 0.1500000 -.0315300
 0.2000000 -.0328400
 0.3000000 -.0326600
 0.4000000 -.0306800
 0.5000000 -.0279000
 0.6000000 -.0241200
 0.7000000 -.0187400
 0.8000000 -.0131600
 0.9000000 -.0071800
 0.9500000 -.0037900
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for BOEING 106 AIRFOIL (boe106-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   boe106-il50,000929.7 at α=10.25°Mach=0 Ncrit=9Xfoil predictionDetails
   boe106-il50,000532.5 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   boe106-il100,000951.6 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   boe106-il100,000552.8 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   boe106-il200,000972.1 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   boe106-il200,000570.2 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   boe106-il500,000998.8 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   boe106-il500,000592 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   boe106-il1,000,0009118.8 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   boe106-il1,000,0005108.2 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
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