2 edition of interaction of an oblique shock wave with a laminar boundary wave found in the catalog.
interaction of an oblique shock wave with a laminar boundary wave
United States. National Aeronautics and Space Administration.
|Statement||by R.J. Hakkinen [and others].|
|Contributions||Hakkinen, Raimo Jaako.|
We investigate the nonmodal physical mechanisms responsible for transient growth in a hypersonic laminar boundary layer and in the interaction of this boundary layer with an incident oblique shock wave. The optimal disturbances and growth curves are computed using an adjoint looping approach. Abstract We investigate flow instability created by an oblique shock wave impinging on a Mach laminar boundary layer at a transitional Reynolds number. The adverse pressure gradient of the oblique shock causes the boundary layer to separate from the wall, resulting in the formation of a recirculation bubble.
Effect of leading edge bluntness on the interaction of ramp induced shock wave with laminar boundary layer at hypersonic speed Computers & Fluids, Vol. 96 Flow control of an oblique shock wave reflection with micro-ramp vortex generators: Effects of location and size. 2D and 3D interaction between an oblique shock wave and a laminar boundary layer on a ﬂat plate. Interest is mainly focused on the unsteady behavior observed in the interaction region. ⇤Graduate Research Assistant, Aerospace Engineering and Mechanics, AIAA Student Member. †Assistant Professor, Aerospace Engineering and Mechanics, AIAA Member.
Shock wave/boundary-layer interactions (SWBLIs) are commonly encountered in high-speed ﬂows over complex geometries that involve intakes, control surfaces, and junctions. An oblique shock wave impinging on the ﬂat-plate boundary layer is a canonical setup used to investigate the resulting ﬂow separation and reattachment in SWBLI [1,2]. In the aeronautical and aerospace industries, the flow configurations where an incident oblique shock wave impinges upon a boundary layer are very common. The supersonic flow around an aircraft, in a rocket nozzle or in a supersonic inlet are some examples among others.
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An investigation of an oblique shock wave/laminar boundary layer interaction is presented. The Mach number wasthe Reynolds number was 10 5 and the overall pressure ratio was The interation has been demonstrated to be laminar and nominally by: the rst shock wave shows less than one percent di erence for any ow parameter in comparison with oblique shock wave theory.
In both cases, the ow is assumed to be laminar. The computed heat transfer distribution agrees closely with the experiment at the time reported by experiment where the ow reaches steady state; however, sig-Cited by: The interaction of an oblique shock wave and a laminar boundary layer developing over a flat plate is investigated by means of numerical simulation and global linear-stability analysis.
Under the selected flow conditions (free-stream Mach numbers, Reynolds numbers and shock-wave angles), the incoming boundary layer undergoes separation due to the adverse pressure by: Boundary Layer Shock Wave Mathematical Method Wave Interaction Laminar Boundary Layer These keywords were added by machine and not by the authors.
This process is experimental and the keywords may be updated as the learning algorithm by: 5. A recent study by Guiho et alinvestigated the interaction of an oblique shock wave with a laminar Mach boundary layer by means of numerical simulation and global stability analysis (GSA).
They showed that the unsteadiness of a SWBLI is mainly associated with instabilities arising from the shear layer. For a separated shock laminar boundary layer interaction, non-periodic self-excited oscillations arise which can result in a significant reduction in the extent of the time-averaged separation region.
of an oblique shock on a laminar boundary layer developed along a flat plate. The flow conditions are freestream Mach number ofshock flow deflection angle 6º, and Reynolds number ReL(based on the distance from the plate leading edge to the inviscid shock impingement location) equal to ´ 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.
Webb, “ Control of the interaction between an oblique shock wave and a supersonic turbulent boundary layer by localized arc filament plasma actuators,” Ph.D. dissertation (The Ohio State University, ). In par- ticular, for the case of an oblique shock wave incident upon a laminar boundary layer, this idea has been used by many investigators to predict that the initial pressure rise near separation is O(R-4).
Unsteady effects of strong shock-wave/boundary-layer interaction at high Reynolds number - Volume - Vito Pasquariello, Stefan Hickel, Nikolaus A. Adams. Guiho, F., Alizard, F.
& Robinet, J.-Ch. Instabilities in oblique shock wave/laminar boundary-layer interactions. BL2 - Shock-wave/laminar boundary layer interaction Florent Renac, ONERA @ General description This test case considers the interaction between an incident oblique shock wave impinging a laminar boundary layer developing over a flat plate (see Figure 1).
The interaction. Results of numerical simulation of interaction between an oblique shock wave and a turbulent boundary layer formed in a supersonic (Mach number M =5) flow past a flat plate are presented. The computations are performed for three cases of interaction of different intensity, which result in an attached or detached flow.
Abstract. The effect of transition location on the interaction between an oblique shock-wave and a boundary-layer at \(M = \) on a flat plate is investigated via direct numerical simulations. It is shown that the shock trips transition at the impingement location and the effect of the impingement location on the separation is studied for laminar, transitional and turbulent interactions.
An incident oblique shock at the shock angle of σ = 35 deg and shock strength of p2/p1= impinges on a laminar boundary layer that evolves from a Blasius profile. The boundary layer separation due to the shock impingement leads to G ̈ortler-like instability, where the nominally two-dimensional and steady inflow undergoes flow transition, giving rise to a three-dimensional and unsteady interaction.
The effect of flow confinement on laminar shock-wave/boundary-layer interactions - Volume - David J. Lusher, Neil D. Sandham. The principal objective of this paper is to study some unsteady characteristics of an interaction between an incident oblique shock wave impinging on a laminar boundary layer developing on a flat.“ The Interaction of an Oblique Shock Wave with a Laminar Boundary Layer Revisited.
An Experimental and Numerical Study,” Journal of Fluid Mechanics, Vol.April. Abstract. The interaction between an impinging oblique shock–wave and a laminar boundary layer on a flat plate is investigated using direct numerical simulations.
The two–dimensional separation bubble resulting from the shock boundary layer interaction (SBLI) at freestream Mach number of for the approach flow is investigated in detail. Experimental studies of a transitional shock-wave--boundary-layer interaction identify robust streaklike flow structures.
In order to account for the emergence of these three-dimensional flow features, growth of small initial perturbations around the two-dimensional laminar base flow is examined. The most significant transient amplification originates from the upstream streamwise vortices.
Book Search tips Selecting this option will search all publications across the Scitation and D. A. Levin, “ On the unsteadiness of shock-laminar boundary layer interactions of hypersonic flows over a double Z. W. Hu, and W.
D. Liu, “ Numerical study of oblique shock-wave/boundary-layer interaction considering sidewall effects.As was discussed in Sectionoblique shock interactions often originate from a wall modification such as a compression corner, or from the generation of a shock outside of the boundary layer with a shock generator.
Passive methods such as (mechanical) VGs with different arrangements, such as Wheeler doublets (see McCormick, ), and also porous surfaces can be used for control (Délery.The existence of the critical angles and the angle limitation of an incident plane wave were clarified.
Incident plane waves exhibited limited wave angles than ordinary plane waves. Ideally, an incident plane wave before the shock wave should propagate downstream while the one behind the shock wave should propagate upstream towards the shock wave.