Shock wave-turbulent boundary layer interaction in hypersonic flow. by Michael S. Holden

Cover of: Shock wave-turbulent boundary layer interaction in hypersonic flow. | Michael S. Holden

Published by Aerospace Research Laboratories in Wright Patterson Air Force Base, Ohio .

Written in English

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Book details

SeriesARL 73-0137
ContributionsUnited States. Aerospace Research Laboratories.
ID Numbers
Open LibraryOL18950426M

Download Shock wave-turbulent boundary layer interaction in hypersonic flow.

Layers of near space, the shock wave/turbulent boundary layer interaction (STBLI) of internal and external aerodynamics become more obvious (Zhang et al., ; Huang et al., ).

Oblique STBLI. Shock wave-boundary-layer interaction (SBLI) is a fundamental phenomenon in gas dynamics that is observed in many practical situations, ranging from transonic aircraft wings to hypersonic vehicles and engines.

Strong interactions of shock waves with boundary layers lead to flow separations and enhanced heat transfer rates. When the approaching boundary layer is hypersonic and transitional the problem is particularly challenging and more reliable data is required in order to assess changes in the flow and the surface heat transfer, and to develop simplified by: In high-speed propulsion systems, shock-boundary layer interaction (SBLI) can occur in intakes, supersonic combustion chambers and nozzles.

Computational fluid dynamics (CFD) is routinely used to study SBLI flows and predict such interactions in geometries of practical interest. Hypersonic Shock wave-turbulent boundary layer interaction in hypersonic flow. book interaction database. Uncertainty Assessments of 2D and Axisymmetric Hypersonic Shock Wave - Turbulent Boundary Layer Interaction Simulations at Compression Corners.

Experimental study of roughness effects on the separated flow over a backward-facing step. Shock Wave/Boundary Layer Interaction (SBLI) is a fundamental phenomenon in gasdynamics and frequently a defining feature in high speed aerodynamic flowfields.

The interactions can be found in practical situations, ranging from transonic aircraft wings to hypersonic vehicles and s: 2. The fluid–structure interaction of a flexible panel exposed to a ramp-induced shock-wave/boundary-layer interaction (SWBLI) at Mach 6 is investigated experimentally for transitional and turbulent incoming boundary by: 2.

Ideal gas shock wave turbulent boundary layer interactions in supersonic flows and their modeling - three dimensional interactions Doyle D. Knight and Alexander A. Zheltovodov Experimental studies of shock wave/boundary layer interactions in hypersonic flows Michael S.

Holden The amplification of turbulence is a key feature in shock-wa ve/turbulence interaction (SWTI) and shock-wave/turbulent boundary layer interaction (SWTBLI), which is closely connected to flow. The shock wave/boundary-layer interaction (SWBLI) occurs in supersonic and hypersonic practical flows such as scramjet inlets, re-entry vehicles, nozzles and launch vehicles, and it would result in boundary-layer thickening and can trigger separation and high-wall heat flux in the internal and external flow fields, especially in the flowpath of the airbreathing hypersonic propulsion system.

Experimental data for a series of two-dimensional hypersonic impinging shock wave / turbulent boundary layer interaction flows at M = 5 are presented. The data consist of surface measurements. A study is presented of the characteristics of transitional and turbulent layers, and regions of shock wave-turbulent boundary layer interaction in high Reynolds number hypersonic flow.

An examination and correlation of skin friction, heat transfer and pressure measurements in laminar, transitional and turbulent boundary layers on sharp flat plates and cones are presented for the Mach range.

Shock wave–boundary-layer interaction (SBLI) is a fundamental phenomenon in gas dynamics that is observed in many practical situations, ranging from transonic aircraft wings to hypersonic. Shock wave-boundary-layer interaction (SBLI) is a fundamental phenomenon in gas dynamics that is observed in many practical situations, ranging from transonic aircraft wings to hypersonic vehicles.

Fig. Supersonic flow through a sharp concave corner: The flow is from left to right at a downstream Mach number of The holographic interferogram shows flow turning through an angle of 11° thereby forming an oblique shock wave that interacts with the turbulent boundary layer.

Shock wave turbulent boundary layer interaction (STBLI) over a flexible panel is investigated by performing large eddy simulations (LES). The supersonic flow is at Mach 4 and unit Reynolds number of × 10 7 (/m).

The incident oblique shock with the shock strength p 3 /p 1 ≈ and shock angle σ ≈ 30 deg impinges near the mid-chord. Shock wave-boundary-layer interaction (SBLI) is a fundamental phenomenon in gas dynamics that is observed in many practical situations, ranging from transonic aircraft wings to hypersonic vehicles and engines.

SBLIs have the potential to pose serious problems in a flowfield; hence they often prove. This work presents an assessment of the experimental data on separated flow in shock wave turbulent boundary layer interactions at hypersonic and supersonic speeds.

The data base consist of selected configurations where the only characteristic length in the interation is the incoming boundary layer. Direct numerical simulation (DNS) of shock wave/turbulent boundary layer interaction (SWTBLI) with pulsed arc discharge is carried out in this paper.

The subject in the study is a Ma= compression flow over a degree ramp. The numerical approaches were validated by the experimental results in the same flow conditions. The heat source model was added to the Navier-Stokes equation. Hypersonic shock wave transitional boundary layer interactions can result in significantly greater peak surface heat transfer than laminar or turbulent interactions.

Consequently, the understanding of the flowfield structure of hypersonic shock wave transitional boundary layer interactions is important. The need for better understanding of the low-frequency unsteadiness observed in shock wave/turbulent boundary layer interactions has been driving research in this area for several decades.

This work investigates the interaction between an impinging oblique shock and a supersonic turbulent boundary layer via large-eddy simulations. The separation length of shock wave/boundary layer interaction (SWBLI) was studied by a numerical method, which was validated by experimental results.

The computational domain was two-dimensional (2-D). The flow field was an incident oblique shock interacting with a turbulent boundary layer on a flat adiabatic plate. According to the simulation data, the dependency of the separation length on. 73rd Annual Meeting of the APS Division of Fluid Dynamics.

Experimental studies of hypersonic shock-wave boundary-layer interactions Two classes of shock-wave boundary-layer interactions were studied experimentally in a shock tunnel in which a low Reynolds number, turbulent flow at Mach 8 was developed on a cold, flat test surface.

The two classes of interactions were: (1) a swept interaction generated by a wedge ('fin') mounted perpendicularly on the. We investigate a full 3-D transitional shock wave boundary layer interaction over a flexible panel by performing high-fidelity direct numerical simulations.

A nominally 2-D laminar boundary layer at Mach number 2 interacts with an oblique shock wave with the shock angle of 35 deg and shock strength of (p3/p1) in the presence of flexible panel. next section we describe the flow physics of shock-wave/turbulent boundary-layer interaction region.

In the last section we correlate flow physics with surface properties and compare the computed wall pressure and skin-friction with the experiments [10]. 2 Test case Single−Fin Flow Origin Fin−tip z x y o Flat−plate wave Inviscid shock.

This technical brief presents a flow separation mitigation device, called cavity-recirculator that can be used to control flow separation during shock wave–boundary layer interaction (SBLI) in high-speed intake flows.

On the unsteadiness of shock–laminar boundary layer interactions of hypersonic flows over a double cone Physics of Fluids 30 “ An instability in supersonic boundary-layer flow over a compression ramp,” J.

Fluid “ Low-frequency unsteadiness of shock wave/turbulent boundary layer interactions,” Annu. Rev. Fluid. mechanisms of the interaction will be illustrated. Much can be learned by consideration of the simp- ler problem of laminar flow over a flat plate stud- ied here and by other authors.

Previous analyses of shock boundary layer interactions have been. Get this from a library. Flow separation in shock wave boundary layer interactions at hypersonic speeds. [A Hamed; Joint Institute for Advancement of Flight Sciences.; Langley Research Center.].

Shock Wave/Boundary Layer Interaction (SBLI) is a fundamental phenomenon in gasdynamics and frequently a defining feature in high speed aerodynamic flowfields. The interactions can be found in practical situations, ranging from transonic aircraft wings to hypersonic vehicles and engines.

Ideal gas shock wave turbulent boundary layer interactions in supersonic flows and their modeling - three dimensional interactions Doyle D.

Knight and Alexander A. Zheltovodov; 6. Experimental studies of shock wave/boundary layer interactions in hypersonic flows.

"This is the first book devoted solely to the phenomenon of Shock Wave Boundary Layer Interactions and covers all flow regimes where SBLI's occur"--Provided by publisher. "Shock Wave/Boundary Layer Interaction (SBLI) is a fundamental phenomenon in gas dynamics and frequently a defining feature in high speed aerodynamic flowfields.

In this work, hypersonic flow over the double-fin geometry (Kussoy and Horstman, ) characterized by three-dimensional intersecting shock-waves/turbulent boundary-layer interaction at Mach is numerically simulated using wall modeled large eddy simulation (WMLES) in.

Documentation of Two- and Three-dimensional Hypersonic Shock Wave/turbulent Boundary Layer Interaction Flows Marvin I. Kussoy National Aeronautics and Space Administration, Ames Research Center, - Aerodynamics, Hypersonic - 26 pages. Shock Wave-Boundary Layer Interaction (SBLI) is a phenomenon occurring in high-speed propulsion systems that is highly undesirable.

Numerous methods have been tested to manipulate and control SBLI which includes both active and passive flow control techniques.

To determine the improvements brought by the flow control techniques, advanced and state-of the-art flow diagnostics and experimental.

This work investigates the self-excited spanwise homogeneous perturbations arising in a shock-wave/boundary-layer interaction (SWBLI) system formed in a hypersonic flow of molecular nitrogen over a double wedge using the kinetic Direct Simulation Monte Carlo (DSMC) method.

Shock wave-boundary-layer interaction (SBLI) is a fundamental phenomenon in gas dynamics that is observed in many practical situations, ranging from transonic aircraft wings to hypersonic vehicles.

Unsteadiness of Shock Wave / Turbulent Boundary Layer Interactions Unsteadiness of Shock Wave / Turbulent Boundary Layer Interactions Noel Clemens Department of Aerospace Engineering and Engineering Mechanics The University of Texas at Austin Acknowledgements David Dolling, B.

Ganapathisubramani, Steve Beresh. The interaction of a spatially developing adiabatic boundary layer flow at M ∞ = and Re θ = with an impinging oblique shock wave (β = °) is analyzed by means of direct numerical simulation of the compressible Navier-Stokes equations.

Under the selected flow conditions the incoming boundary layer undergoes mild separation due to the adverse pressure gradient. Shock wave boundary layer interactions during inlet unstart Development of low/no bleed inlets hold the key to future hypersonic technology.

Without bleed the inlets are highly prone unstart, which is the disgorging of shock train within the inlet/isolatorsection of the scramjet to cause massive loss in thrust and fatal accidents.Shock wave-boundary-layer interaction (SBLI) is a fundamental phenomenon in gas dynamics that is observed in many practical situations, ranging from transonic aircraft wings to hypersonic vehicles and engines.

SBLIs have the potential to pose serious problems in a flowfield; hence they often prove to be a critical - or even design limiting - issue for many aerospace applications. This is the.NASA-CR, a database report on hypersonic shock wave / turbulent boundary-layer interactions, was the product of phase 1 of that effort.

Phase 2 produced a similar database, NASA-CR, covering the topics of attached hypersonic boundary layers in pressure gradients and compressible turbulent mixing layers.

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