Accession Number N20130011041
Title Effect of Boundary-Layer Bleed Hole Inclination Angle and Scaling on Flow Coefficient Behavior.
Publication Date Feb 2013
Media Count 24p
Personal Author D. O. Davis J. W. Slater M. A. Vyas M. B. Eichorn P. J. Barnhart
Abstract Phase II data results of the Fundamental Inlet Bleed Experiments study at NASA Glenn Research Center are presented which include flow coefficient behavior for 21 bleed hole configurations. The bleed configurations are all round holes with hole diameters ranging from 0.795 to 6.35 mm, hole inclination angles from 20deg to 90deg, and thickness-to-diameter ratios from 0.25 to 2.0. All configurations were tested at a unit Reynolds number of 2.46 10(exp 7)/m and at discrete local Mach numbers of 1.33, 1.62, 1.98, 2.46, and 2.92. Interactions between the design parameters of hole diameter, hole inclination angle, and thickness-to-diameter as well as the interactions between the flow parameters of pressure ratio and Mach number upon the flow coefficient are examined, and a preliminary statistical model is proposed. An existing correlation is also examined with respect to this data.
Keywords Boundary layers
Design analysis
Flow characteristics
Flow coefficients
Inlet flow
Mach number
Mathematical models
Pressure ratio
Reynolds number
Supersonic inlets
Thickness ratio

Source Agency National Aeronautics and Space Administration
NTIS Subject Category 51A - Aerodynamics
72B - Algebra, Analysis, Geometry, & Mathematical Logic
Corporate Author National Aeronautics and Space Administration, Cleveland, OH. NASA John H. Glenn Research Center at Lewis Field.
Document Type Technical report
Title Note N/A
NTIS Issue Number 1320
Contract Number N/A

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