Author: Amado Arthur TrujilloPublisher:
ISBN:
Category :
Languages : en
Pages : 254
Book Description
Experimental Investigation of the Interaction of an Oblique Shock Wave with a Turbulent Boundary Layer
Author: Amado Arthur TrujilloPublisher:
ISBN:
Category :
Languages : en
Pages : 254
Book Description
Experimental Investigation of the Interaction of a Plane, Oblique, Incident-reflecting Shock Wave with a Turbulent Boundary Layer on a Cooled Surface. Volume 3 - Tabulated Data
Author: Experimental Investigation of the Interaction of a Plane, Oblique, Incident-reflecting Shock Wave with a Turbulent Boundary Layer on a Cooled Surface. Volume 1 - Test Description and Data Summary
Author: Experimental Investigation of the Interaction of a Plane, Oblique, Incident-reflecting Shock Wave with a Turbulent Boundary Layer on a Cooled Surface. Volume 2 - Basic Plotted Data
Author: 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.
Oblique Shock Wave/Turbulent Boundary Layer Interactions in Three Dimensions at Mach 3
Author: B. OskamPublisher:
ISBN:
Category :
Languages : en
Pages : 181
Book Description
The second phase of a detailed experimental investigation has been carried out on the interaction between oblique shock waves and turbulent boundary layers in three dimensions. The present work extends the original region of study of the shock wave interaction area towards the streamwise corner between the shock generator and the test wall. The purpose of this report is to present the experimental data in tabulated form. The tabulations include both surface data such as heat transfer and static pressure as well as detailed flow field surveys of pitot pressure, flow angularity, static pressure and total temperature.
An Experimental Investigation of Shock Wave -- Boundary Layer Interaction Dynamics
Author: Gerald W. BraunPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 254
Book Description
Wind tunnel tests were performed which simulated the flow pulsations which are sometimes produced in engine inlets by shock-boundary layer interaction. Shock Mach numbers from 1.2 to 1.4 were used and the boundary layer was influenced by air bleeding in or sucking off. The flow was observed by shodowgraph and static and total pressures were measured by means of low frequency and high frequency response instruments. Static wall pressures, boundary layer pressure profiles, and total pressure distributions across several tunnel cross sections were plotted. The data were analyzed with respect to their rms value and power spectral density. A literature survey and an analytical investigation of the pulsations in a diffuser with nonviscous flow are included. (Author).
Experimental and Numerical Investigation of an Oblique Shock Wave/turbulent Boundary Layer Interaction with Continuous Suction
Author: Driss BenhachmiAn Experimental Investigation of Shock Wave-turbulent Boundary Layer Interactions with and Without Boundary Layer Suction
Author: C. C. SunPublisher:
ISBN:
Category : Shock waves
Languages : en
Pages : 916
Book Description
Tabulated data from a series of experimental studies of the interaction of a shock wave with a turbulent boundary layer in axisymmetric flow configurations is presented. The studies were conducted at the walls of circular wind tunnels and on the cylindrical centerbody of an annular flow channel. Detailed pitot pressure profiles and wall static pressure profiles upstream of, within and downstream of the interaction region are given. Results are presented for flows at nominal freestream Mach Numbers of 2, 3 and 4. For studies at the tunnel sidewalls, the shock waves were produced by conical shock generators mounted on the centerline of the wind tunnel at zero angle of attack. The annular ring generator was used to produce the shock wave at the centerbody of the annular flow channel. The effects of boundary layer bleed were examined in the investigation. Both bleed rate and bleed location were studied. Most of the bleed studies were conducted with bleed holes drilled normal to the wall surface but the effects of slot suction were also examined. A summary of the principal results and conclusions is given.
Author: David William Kuntz