Journal ArticleDOI
Survey of Validation Data Base for Shockwave Boundary-Layer Interactions in Supersonic Inlets
Awatef Hamed,J. S. Shang +1 more
TLDR
In this paper, the authors review and assess the data base for shock boundary-layer interaction that is pertinent to the flow prediction in supersonic inlets and identify specific areas related to shock wave/boundary layer interaction bleed, for flow separation control.Abstract:
The performance of supersonic inlets is strongly affected by the boundary-layer development over its internal surfaces. Boundary-layer bleed is used to suppress separation and to provide the desired inlet performance. The gain in pressure recovery and stability is accompanied, however, with a loss in mass flow and an increase in drag that must be minimized by optimizing the amount of bleed and bleed configuration. The purpose of this work is to review and assess the data base for shock boundary-layer interaction that is pertinent to the flow prediction in supersonic inlets. The first part of the review concerns mixed compression supersonic inlets and their bleed system performance at design and off-design conditions. Based on the assessment of this data, specific areas related to shock wave/boundary-layer interaction bleed, for flow-separation control, are identified, the last part of the review addresses this phenomena in various twoand three-dimensional flow configurations. The effect of bleed in the interaction zone is especially emphasized.read more
Citations
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Journal ArticleDOI
Shock Train Leading-Edge Detection in a Dual-Mode Scramjet
TL;DR: In this paper, the authors used time-resolved pressure measurements in a dual-mode scramjet isolator to investigate the potential for using the measurements for shock train leading-edge detection.
Journal ArticleDOI
Unstart Detection in a Simplified-Geometry Hypersonic Inlet-Isolator Flow
TL;DR: In this paper, an unstart detection technique based on high-frequency pressure measurements made in a hypersonic inlet-isolator model is investigated, and the results indicate that the power-spectrum-based algorithm implemented close to the isolator exit is more sensitive to the onset of unstart, whereas the pressure-magnitude-change criterion gives earlier detection in many cases.
Journal ArticleDOI
Three-dimensional shock-wave/boundary-layer interactions with bleed
TL;DR: In this paper, the authors investigated the physics of three-dimensional, shockwave/boundary-layer interactions on a flat plate in which fluid in the boundary layer was bled through a circular hole into a plenum to control shock-wave induced flow separation.
Journal ArticleDOI
Control of shock-wave/boundary-layer interactions by bleed
TL;DR: In this paper, the authors investigated the effect of bleed in controlling barrier/boundary layer interactions on a flat plate with a focus on understanding how bleed-hole angle, presence of upstream and downstream bleed holes, and pressure ratio across bleed holes affect structure of barrier shock, surface pressure distribution, and bleed rate (in terms of flow coefficient).
Journal ArticleDOI
Simulation of Shock/Boundary-Layer Interactions with Bleed Using Immersed-Boundary Methods
TL;DR: In this article, an immersed boundary (IB) method was used to simulate the effects of arrays of discrete bleed ports in controlling shock wave / turbulent boundary layer inter actions. Both Reynolds averaged Navier-Stokes (RANS) and hybrid large-eddy / Reynolds-averaged Navier -Stokes(LES/RANS), turbulence closures are used with the IB technique.
References
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Investigation of separated flows in supersonic and subsonic streams with emphasis on the effect of transition
TL;DR: In this paper, the results of experimental and theoretical research conducted on flow separation associated with steps, bases, compression corners, curved surfaces, shock-wave boundary-layer reflections, and configurations producing leading-edge separation are presented.
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Shock wave/turbulent boundary layer interaction and its control
TL;DR: In this paper, a review of the fundamental properties of the interaction between a shock wave and a boundary layer is presented, with emphasis on the physics of phenomena involved in this process.
Journal ArticleDOI
Unsteadiness of the Separation Shock Wave Structure in a Supersonic Compression Ramp Flowfield
David S Dolling,M. T. Murphy +1 more
TL;DR: In this paper, wall pressure fluctuations have been measured in a two-dimensional separated compression ramp-induced shock wave turbulent boundary-layer interaction at a nominal freestream Mach number of 3 and at Reynolds numbers based on boundary layer thickness of 78 X 10 and 14x 10.
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Detailed Study of Attached and Separated Compression Corner Flowfields in High Reynolds Number Supersonic Flow
TL;DR: In this article, an experimental study has been carried out to detail the interaction of a compressible turbulent boundary layer with shock waves of varying strengths, produced by two-dimensional al compression corners of 8, 16, 20, and 24 deg angles.