Two-dimensional Compression Corner and Planar Shock Wave Interactions with a Supersonic, Turbulent Boundary Layer PDF Download

Author: C. Herbert Law
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 120

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Author: C. Herbert Law
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 118

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Book Description
Experimental data have been obtained to describe the interactions between a turbulent boundary layer and (1) a two-dimensional compression corner and (2) an externally generated planar shock wave. Investigations were conducted at Mach number 3 over a range of Reynolds numbers from 10 to 100 million under adiabatic wall conditions. The effects of compression corner angle, planar shock wave strength, and Reynolds number on the length of separation and upstream influence were obtained. The incipient separation conditions and three-dimensional effects were also investigated. The separation and upstream influence lengths were found to increase with increasing Reynolds number for fixed overall pressure rise. The overall pressure rise for incipient separation is approximately the same for the compression corner interaction and the planar shock wave interaction, and increases with increasing Reynolds number. Turbulent boundary layer separation was found to be of the free interaction type, whereby the separation angle and the pressure distribution through separation were found to be independent of Reynolds number, overall pressure rise, and type of disturbance. For the case of the externally generated shock wave, the span of the shock generator had to be reduced in order to eliminate an initially significant influence of the sidewall shock wave-boundary layer interaction on the test region. (Author).

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

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Book Description
Experimental data have been obtained to describe the interactions between a turbulent boundary layer and (1) a two-dimensional compression corner and (2) an externally generated planar shock wave. Investigations were conducted at Mach number 3 over a range of Reynolds numbers from 10 to 100 million under adiabatic wall conditions. The effects of compression corner angle, planar shock wave strength, and Reynolds number on the length of separation and upstream influence were obtained. The incipient separation conditions and three-dimensional effects were also investigated. The separation and upstream influence lengths were found to increase with increasing Reynolds number for fixed overall pressure rise. The overall pressure rise for incipient separation is approximately the same for the compression corner interaction and the planar shock wave interaction, and increases with increasing Reynolds number. Turbulent boundary layer separation was found to be of the free interaction type, whereby the separation angle and the pressure distribution through separation were found to be independent of Reynolds number, overall pressure rise, and type of disturbance. For the case of the externally generated shock wave, the span of the shock generator had to be reduced in order to eliminate an initially significant influence of the sidewall shock wave-boundary layer interaction on the test region. (Author).

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

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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: Michael Arthur Schwartz
Publisher:
ISBN:
Category : Ultrasonic waves
Languages : en
Pages : 200

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Author: Gary S. Settles
Publisher:
ISBN:
Category :
Languages : en
Pages : 30

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Basic experimental research was conducted in two and three-dimensional shock wave/boundary layer interactions and associated turbulence measurements. The primary emphasis has been in exploring the important but little-known range of three-dimensional interactions at high speeds. Building on previous work, a series of parametric experiments and a detailed analysis have led to the synthesis of scaling laws for Reynolds number effects on these interactions. Further experiments continued the adaptation and use of hot-wire anemometry in high-Reynolds number supersonic flows. Hot-wire surveys were made in the previously-explored flowfield of a reattaching free shear layer, and in the interaction generated by a two-dimensional compression corner of 8 deg deflection angle at Mach 3. Other research activities, including technique, instrumentation, and facility development are summarized in this report.

Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1102

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Author: Alexander J. Smits
Publisher: Springer Science & Business Media
ISBN: 0387263055
Category : Science
Languages : en
Pages : 418

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Book Description
A good understanding of turbulent compressible flows is essential to the design and operation of high-speed vehicles. Such flows occur, for example, in the external flow over the surfaces of supersonic aircraft, and in the internal flow through the engines. Our ability to predict the aerodynamic lift, drag, propulsion and maneuverability of high-speed vehicles is crucially dependent on our knowledge of turbulent shear layers, and our understanding of their behavior in the presence of shock waves and regions of changing pressure. Turbulent Shear Layers in Supersonic Flow provides a comprehensive introduction to the field, and helps provide a basis for future work in this area. Wherever possible we use the available experimental work, and the results from numerical simulations to illustrate and develop a physical understanding of turbulent compressible flows.

Author: Konstantinos Kontis
Publisher: Springer Science & Business Media
ISBN: 3642256856
Category : Science
Languages : en
Pages : 1122

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The University of Manchester hosted the 28th International Symposium on Shock Waves between 17 and 22 July 2011. The International Symposium on Shock Waves first took place in 1957 in Boston and has since become an internationally acclaimed series of meetings for the wider Shock Wave Community. The ISSW28 focused on the following areas: Blast Waves, Chemically Reacting Flows, Dense Gases and Rarefied Flows, Detonation and Combustion, Diagnostics, Facilities, Flow Visualisation, Hypersonic Flow, Ignition, Impact and Compaction, Multiphase Flow, Nozzle Flow, Numerical Methods, Propulsion, Richtmyer-Meshkov, Shockwave Boundary Layer Interaction, Shock Propagation and Reflection, Shock Vortex Interaction, Shockwave Phenomena and Applications, as well as Medical and Biological Applications. The two Volumes contain the papers presented at the symposium and serve as a reference for the participants of the ISSW 28 and individuals interested in these fields.

Author: Doyle D. Knight
Publisher:
ISBN:
Category : Navier-Stokes equations
Languages : en
Pages : 80

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