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Numerical Simulation of Inlet Bleed with Circular Holes on Plate Under Shock-Wave/Boundary-Layer InteractionsA numerical study was performed to investigate the shock-wave/boundary-layer interactions on a flat plate with bleed through one or more circular holes that vent into a plenum. The bleed-hole patterns considered for the study include in-line multiple holes and staggered multiple-row holes that are configured to simulate the patterns used in inlet bleed systems of high performance aircraft. The focus of the study was to examine how the bleed through multiple holes affect bleed rate and the pressure and Mach number distributions. Since the bleed performance was found sensitive to the change in bleed conditions, a computational procedure was developed to give a good turnaround computational time for parametric studies involving changes in bleed hole geometry and the structure of shock-wave/boundary-layer flowfield. The procedure includes the grid-generation methodology and the flow simulation with solutions from the Navier-Stokes equations. The computational techniques permit analysis of complex bleed systems and make possible the investigation of a broader range of design variables associated with inlet bleed operation.
Document ID
20020006058
Acquisition Source
Ames Research Center
Document Type
Conference Paper
Authors
Chyu, Wei J.
(NASA Ames Research Center Moffett Field, CA United States)
Rimlinger, Mark J.
(Carnegie-Mellon Univ. Pittsburgh, PA United States)
Shih, Tom I.-P.
(Carnegie-Mellon Univ. Pittsburgh, PA United States)
Date Acquired
August 20, 2013
Publication Date
January 1, 1994
Subject Category
Fluid Mechanics And Thermodynamics
Meeting Information
Meeting: NASA Workshop on Surface Modeling, Grid Generation and Related Issues in CFD Solutions
Location: Cleveland, OH
Country: United States
Start Date: May 9, 1995
End Date: May 11, 1995
Sponsors: NASA Headquarters
Funding Number(s)
CONTRACT_GRANT: NAG2-709
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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