Author: Michael S. HoldenPublisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Experimental Studies of Laminar Separated Flows Induced by Shock Wave/boundary Layer and Shock/shock Interaction in Hypersonic Flows for CFD Validation
Author: Michael S. HoldenShock Wave-Boundary-Layer Interactions
Author: Holger BabinskyPublisher: Cambridge University Press
ISBN: 9781107646537
Category : Technology & Engineering
Languages : en
Pages : 480
Book Description
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. SBLI's have the potential to pose serious problems and is thus a critical issue for aerospace applications. This is the first book devoted solely to a comprehensive, state of the art explanation of the phenomenon with coverage of all flow regimes where SBLI's occur. The book includes contributions from leading international experts who share their insight into SBLI physics and the impact of these interactions on practical flow situations. This book is aimed at practitioners and graduate students in aerodynamics who wish to familiarise themselves with all aspects of SBLI flows. It is a valuable resource for the specialist because it gathers experimental, computational and theoretical knowledge in one place.
Flow Separation in Shock Wave Boundary Layer Interactions at Hypersonic Speeds
Author: Awatef HamedPublisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 52
Book Description
A Study of Flow Separation in Regions of Shock Wave-boundary Layer Interaction in Hypersonic Flow
Author: Michael S. HoldenPublisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 96
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.
Shock Wave-Boundary-Layer Interactions
Author: Holger BabinskyPublisher: Cambridge University Press
ISBN: 1139498649
Category : Technology & Engineering
Languages : en
Pages : 481
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.
An Experimental Documentation of a Hypersonic Shock-wave Turbulent Boundary Layer Interaction Flow: With and Without Separation
Author: DSMC Simulation of Separated Flows about Flared Bodies at Hypersonic Conditions
Author: James N. MossPublisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 30
Book Description
This paper describes the results of a numerical study of interacting hypersonic flows at conditions that can be produced in ground-based test facilities. The computations are made with the direct simulation Monte Carlo (DSMC) method of Bird. The focus is on Mach 10 flows about flared axisymmetric configurations, both hollow cylinder flares and double cones. The flow conditions are those for which experiments have been or will be performed in the ONERA R5Ch low-density wind tunnel and the Calspan-University of Buffalo Research Center (CUBRC) Large Energy National Shock (LENS) tunnel. The range of flow conditions, model configurations, and model sizes provides a significant range of shock/shock and shock/boundary layer interactions at low Reynolds number conditions. Results presented will highlight the sensitivity of the calculations to grid resolution, contrast the difference in flow structure for hypersonic cold flows and those of more energetic but still low enthalpy flows, and compare the present results with experimental measurements for surface heating, pressure, and extent of separation.
Flow Separation in Shock Wave Boundary Layer Interactions at Hypersonic Speeds
Author: A. HamedA Computer Study of Hypersonic Laminar Boundary-layer/shock-wave Interaction Using the Time-dependent Compressible Navier-Stokes Equations
Author: B. K. HodgePublisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 52
Book Description
This report presents the results of an investigation of hypersonic laminar boundary-layer/shock-wave interactions using the method of MacCormack to solve the time-dependent compressible Navier-Stokes equations. Comparisons of the numerical solutions with experimental data were made to ascertain the validity of the numerical method and to identify regions of anomalous behavior. The algorithm gave good results when applied to hypersonic laminar interactions that caused either small or no separated regions and marginal performance when applied to hypersonic laminar interactions having large regions of separated flow. The extents of the separated regions in interactions having large regions of separated flow were underpredicted when compared with experimental data. The predicted wall heat-transfer rates exhibited the correct qualitative trend but not the experimentally measured quantitative values. Consideration of the effects of needed stabilizing terms as well as grid resolution suggests inadequate mesh spacing in the longitudinal direction as the cause of the aforementioned anomalies. If inadequate mesh spacing (and the corresponding lack of support for every term of the Navier-Stokes equations) is a prime cause of the cited discrepancies between the numerical results and the experimental data, then the needed reduction of several orders of magnitude in delta x, would increase CPU time and core storage requirements to untenable levels. (Author).
Author: