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Davis AIRFOIL (davis-il)

Davis AIRFOIL - Consolidated/Davis airfoil (B-24 wing?)


Airfoil davis-il
Details Dat file Parser  
(davis-il) Davis AIRFOIL
Consolidated/Davis airfoil (B-24 wing?)
Max thickness 11.3% at 30% chord.
Max camber 3.7% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
Davis AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125000 0.0175000
 0.0250000 0.0268000
 0.0500000 0.0405000
 0.0750000 0.0510000
 0.1000000 0.0600000
 0.1500000 0.0740000
 0.2000000 0.0825000
 0.2500000 0.0875000
 0.3000000 0.0900000
 0.4000000 0.0915000
 0.5000000 0.0860000
 0.6000000 0.0770000
 0.7000000 0.0625000
 0.8000000 0.0460000
 0.9000000 0.0250000
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0125000 -.0105000
 0.0250000 -.0147000
 0.0500000 -.0205000
 0.0750000 -.0240000
 0.1000000 -.0260000
 0.1500000 -.0270000
 0.2000000 -.0265000
 0.2500000 -.0245000
 0.3000000 -.0225000
 0.4000000 -.0176500
 0.5000000 -.0130000
 0.6000000 -.0100000
 0.7000000 -.0075000
 0.8000000 -.0045000
 0.9000000 -.0020000
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for Davis AIRFOIL (davis-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   davis-il50,000922.2 at α=11°Mach=0 Ncrit=9Xfoil predictionDetails
   davis-il50,000536.4 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   davis-il100,000954 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   davis-il100,000555 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   davis-il200,000976.1 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   davis-il200,000572.1 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   davis-il500,0009101.4 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   davis-il500,000591.3 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   davis-il1,000,0009120.8 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   davis-il1,000,0005107 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
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