A Study of Flow Separation in Regions of Shock Wave-boundary Layer Interaction in Hypersonic Flow PDF Download

Author: Michael S. Holden
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 96

View

Book Description
This report describes a theoretical and experimental investigation of the properties of attached and separated regions of shock wave-laminar boundary layer interacting in the strong interaction regime. The flow is studied over a flat plate-wedge compression surface in the high Mach number, low Reynolds number regime where the interaction between the viscous and inviscid regions over the basic flat plate is strong and of fundamental importance to the problem. The theoretical analysis treats the development of the viscous layer and its interaction with the external inviscid stream, using an integral representation for the boundary layer equations. A complementary experimental study investigated the flow over a flat plate-wedge compression surface for a range of free-stream Reynolds number and Mach number conditions in the strong interaction regime.

Author: United States. Air Force. Office of Aerospace Research
Publisher:
ISBN:
Category :
Languages : en
Pages : 0

View

Book Description

Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 0

View

Book Description
This report describes a theoretical and experimental investigation of the properties of attached and separated regions of shock wave-laminar boundary layer interacting in the strong interaction regime. The flow is studied over a flat plate-wedge compression surface in the high Mach number, low Reynolds number regime where the interaction between the viscous and inviscid regions over the basic flat plate is strong and of fundamental importance to the problem. The theoretical analysis treats the development of the viscous layer and its interaction with the external inviscid stream, using an integral representation for the boundary layer equations. A complementary experimental study investigated the flow over a flat plate-wedge compression surface for a range of free-stream Reynolds number and Mach number conditions in the strong interaction regime.

Author: Holger Babinsky
Publisher: Cambridge University Press
ISBN: 1139498649
Category : Technology & Engineering
Languages : en
Pages : 481

View

Book Description
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 first book devoted solely to a comprehensive, state-of-the-art explanation of this phenomenon. It includes a description of the basic fluid mechanics of SBLIs plus contributions from leading international experts who share their insight into their physics and the impact they have in practical flow situations. This book is for practitioners and graduate students in aerodynamics who wish to familiarize themselves with all aspects of SBLI flows. It is a valuable resource for specialists because it compiles experimental, computational and theoretical knowledge in one place.

Author: Awatef Hamed
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 78

View

Book Description

Author: A. Hamed
Publisher:
ISBN:
Category :
Languages : en
Pages : 52

View

Book Description

Author: Robert H. Korkegi
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 60

View

Book Description
The research was designed to gain understanding of the flow of air at high speeds over the components of lifting supersonic and hypersonic vehicles--wings, flaps, fins, inlets--and their interactions with respect to heating, surface friction, pressure, and aerodynamic forces. The objective was to help predict (a) flows on complex aerospace vehicle configurations in high-speed flight and (b) the location of areas of high heating. The research covers the areas of laminar and turbulent boundary layers, boundary layer transition, boundary layer separation, base flows and wakes, low density flows, three-dimensional interactions, viscous flow problems, and some flow measurement techniques.

Author: Paul K. Chang
Publisher: Elsevier
ISBN: 1483181286
Category : Technology & Engineering
Languages : en
Pages : 800

View

Book Description
Interdisciplinary and Advanced Topics in Science and Engineering, Volume 3: Separation of Flow presents the problem of the separation of fluid flow. This book provides information covering the fields of basic physical processes, analyses, and experiments concerning flow separation. Organized into 12 chapters, this volume begins with an overview of the flow separation on the body surface as discusses in various classical examples. This text then examines the analytical and experimental results of the laminar boundary layer of steady, two-dimensional flows in the subsonic speed range. Other chapters consider the study of flow separation on the two-dimensional body, flow separation on three-dimensional body shape and particularly on bodies of revolution. This book discusses as well the analytical solutions of the unsteady flow separation. The final chapter deals with the purpose of separation flow control to raise efficiency or to enhance the performance of vehicles and fluid machineries involving various engineering applications. This book is a valuable resource for engineers.

Author: Michael S. Holden
Publisher:
ISBN:
Category :
Languages : en
Pages : 81

View

Book Description
A study is presented of attached and separated turbulent viscous interaction regions resulting from shock wave-boundary layer interaction in hypersonic flow. The direct measurements of surface shear indicated that turbulent boundary layer separation occurred well before an inflection point was observed in the surface pressure distribution through the interaction region. It was found that the incipient separation conditions for both shock- and wedge-induced interaction regions can be correlated in terms of the local Mach number and the properties of the turbulent boundary layer ahead of the interaction. The length of the separated regions induced both by externally generated shocks and on compression surfaces was found to increase with increasing Reynolds number and wall-to-free stream stagnation temperature and decreasing Mach number of the free stream. Correlations for the plateau pressure and the heat transfer rate at reattachment and in the plateau region are presented. The fluctuating pressure measurements indicated that turbulent viscous interaction regions in separated flow are highly unsteady, and that this unsteadiness is reflected in the observed motion of the separation and reattachment points. (Modified author abstract).

Author: M. S. Holden
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 76

View

Book Description