Download or read book Turbulent Boundary Layer Shock Interaction with and Without Injection written by Edgar Alzner and published by . This book was released on 1970 with total page 175 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experimental results of turbulent boundary layer-shock interaction at Mach 6 using a 10 deg axisymmetric wedge around an axisymmetric centerbody are presented and an effort is made to obtain a simple numerical solution of this problem by the time dependent unsteady method. Static pressure, pitot pressure and total temperature profiles, wall static pressure, heat transfer measurements and optical data were obtained. Air and hydrogen are injected to study their effects on the interaction region. Wall heat transfer and pressure distributions for different injection rates of both air and hydrogen are presented. Detailed mappings of Mach number, pressure distributions and shock wave locations are derived for the air injection as well as the no injection case. Experimental results show a natural boundary layer thickness of about .85 inches, a separated flow region about two inches long and a pressure plateau characteristic of turbulent flow. (Author).
Download or read book Control of Shock Wave turbulent Boundary Layer Interactions Using Tangential Injection written by John F. Donovan and published by . This book was released on 1996 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Shock Wave Boundary Layer Interactions written by Holger Babinsky and published by Cambridge University Press. This book was released on 2011-09-12 with total page 481 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Download or read book Investigation of Laminar and Turbulent Boundary Layers Interacting with Externally Generated Shock Waves written by Earl C. Watson and published by . This book was released on 1969 with total page 140 pages. Available in PDF, EPUB and Kindle. Book excerpt: Laminar and turbulent boundary layer interactions with externally generated shock waves.
Download or read book Three dimensional Interaction of a Swept Shock Wave with a Turbulent Boundary Layer and the Effects of Air Injection on Separation written by David John Peake and published by . This book was released on 1975 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Transition Location Effect on Shock Wave Boundary Layer Interaction written by Piotr Doerffer and published by Springer Nature. This book was released on 2020-07-30 with total page 540 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book presents experimental and numerical findings on reducing shock-induced separation by applying transition upstream the shock wave. The purpose is to find out how close to the shock wave the transition should be located in order to obtain favorable turbulent boundary layer interaction. The book shares findings obtained using advanced flow measurement methods and concerning e.g. the transition location, boundary layer characteristics, and the detection of shock wave configurations. It includes a number of experimental case studies and CFD simulations that offer valuable insights into the flow structure. It covers RANS/URANS methods for the experimental test section design, as well as more advanced techniques, such as LES, hybrid methods and DNS for studying the transition and shock wave interaction in detail. The experimental and numerical investigations presented here were conducted by sixteen different partners in the context of the TFAST Project. The general focus is on determining if and how it is possible to improve flow performance in comparison to laminar interaction. The book mainly addresses academics and professionals whose work involves the aerodynamics of internal and external flows, as well as experimentalists working with compressible flows. It will also be of benefit for CFD developers and users, and for students of aviation and propulsion systems alike.
Download or read book Three dimensional Interaction of a Swept Shock Wave with a Turbulent Boundary Layer and the Effects of Air Injection on Separation written by David John Peake and published by . This book was released on 1975 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Experimental Investigation of Shock Wave turbulent Boundary Layer Interactions with and Without Boundary Layer Suction written by C. C. Sun and published by . This book was released on 1977 with total page 916 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Download or read book An experimental investigation of shock wave turbulent boundary layer interactions with and without boundary layer suction written by Chen-Chih Sun and published by . This book was released on 1977 with total page 916 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Transonic Shock Interaction with a Tangentially Injected Turbulent Boundary Layer written by G. R. Inger and published by . This book was released on 1984 with total page 17 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper describes a non-asymptotic triple deck theory of transonic shock/turbulent boundary layer interaction which takes into account the influence of upstream tangential injection on a curved wall. In addition to Reynolds number and the shock strength, the theory is parameterized by arbitrary values of the incoming boundary layer shape factor, wall jet maximum velocity ratio and the nondimensional height of this ratio; results of a comprehensive parametric study are then presented. It is shown that the wall jet effects significantly reduce both the streamwise scale and displacement thickening of the interaction zone. While increasing the upstream and downstream skin friction levels, these effects also reduce the minimum interactive Cf and thus actually hasten the onset of incipient separation at the shock foot.
Download or read book Two dimensional Compression Corner and Planar Shock Wave Interactions with a Supersonic Turbulent Boundary Layer written by C. Herbert Law and published by . This book was released on 1975 with total page 120 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Experimental Investigation of Shock Wave Boundary Layer Interaction Dynamics written by Gerald W. Braun and published by . This book was released on 1969 with total page 254 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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).
Download or read book Interaction Between a Normal Shock Wave and a Turbulent Boundary Layer at High Transonic Speeds written by Thomas Charles Adamson and published by . This book was released on 1980 with total page 152 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Understanding and Predicting Shockwave and Turbulent Boundary Layer Interactions written by M. Pino Martin and published by . This book was released on 2009 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: Shockwave and turbulent boundary layer interactions produce intense localized pressure loads and heating rates that can have a dramatic influence on the drag and heating experienced by a high-speed vehicle, and can significantly impact fuel mixing and combustion in propulsion systems. The lack of standardized and traceable databases prevents the calibration of computational fluid dynamic models to accurately represent these critical flow phenomena. In this work we accomplished the development and validation against experiments at the same flow and boundary conditions of direct numerical simulations of shock and turbulent boundary layer interactions. We pioneered the development of a unique numerical capability that allows the accurate and detailed three-dimensional turbulence data at a reasonable turn-around time. In turn, parametric studies of fundamental flow physics are feasible, for the first time. By accurate, it is meant that the numerical uncertainty is within the experimental error.
Download or read book Interaction of a Turbulent Boundary Layer with a Normal Shock Wave Followed by an Adverse Pressure Gradient written by W. H. Schofield and published by . This book was released on 1983 with total page 12 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental study was made of the development of a turbulent boundary layer after an interaction with a normal shock wave (strong enough to cause a local separation) in a strong adverse pressure gradient. This type of flow, which occurs in air breathing engine components (e.g. supersonic intakes, transonic compressor stages and supersonic diffusers), is poorly understood and cannot be satisfactorily predicted. The measurements, made in a closed duct, extended well downstream of the shock wave interaction. Detailed results for the flow are presented and used to support two major conclusions. It is shown that the post shock adverse pressure gradient has a large effect on boundary layer development through the interaction and downstream of it. Consequently existing results for interactions without a post shock pressure gradient should not be used as a model for practical flows which typically have strong pressure gradients applied downstream of the shock wave. The second conclusions was that the shock wave in a rectangular duct produced a pronounced stabilising effect on the downstream flow. Surface flow visualization suggests that this stabilization is achieved by streamwise vortices shed into the flow from the separated region formed by the shock wave. Implications of this result to nominally two-dimensional flow situations and to flows with weak interactions without local separations are discussed.
Download or read book Interaction of a shock wave with a boundary layer distributed by injection written by Michael Jonathan Smith and published by . This book was released on 1978 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Surface and Flow Field Measurements in a Symmetric Crossing Shock Wave turbulent Boundary layer Interaction written by D. O. Davis and published by . This book was released on 1992 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:
