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Study Of Three Dimensional Flow Fields Generated By The Interaction Of A Skewed Shock Wave With A Turbulent Boundary Layer
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Book Synopsis Study of Three-dimensional Flow Fields Generated by the Interaction of a Skewed Shock Wave with a Turbulent Boundary Layer by :
Download or read book Study of Three-dimensional Flow Fields Generated by the Interaction of a Skewed Shock Wave with a Turbulent Boundary Layer written by and published by . This book was released on 1975 with total page 207 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Three-dimensional Shock Wave-turbulent Boundary Layer Interactions at Mach 6 by : C. Herbert Law
Download or read book Three-dimensional Shock Wave-turbulent Boundary Layer Interactions at Mach 6 written by C. Herbert Law and published by . This book was released on 1975 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experimental results of an investigation of the three-dimensional interaction between a skewed shock wave and a turbulent boundary layer are presented. Surface pressure and heat transfer distributions and oil flow photographs were obtained at a freestream Mach number of 5.85 and two Reynolds numbers of ten and twenty million per foot. The model configuration consisted of a shock generator mounted perpendicularly to a flat plate. The shock generator leading edge was sharp and nonswept and intersected the flat plate surface about 8.5 inches downstream of the flat plate leading edge. The shock generator surface was 7.55 inches long and 3 inches high and its angle to the freestream flow was adjusted from 4 to 20 degrees. The generated shock waves were of sufficient strength to produce turbulent boundary layer separation on the flat plate surface.
Book Synopsis Three-dimensional Flow Fields Generated by the Interaction of a Swept Shock Wave with a Turbulent Boundary Layer by : Bastiaan Oskam
Download or read book Three-dimensional Flow Fields Generated by the Interaction of a Swept Shock Wave with a Turbulent Boundary Layer written by Bastiaan Oskam and published by . This book was released on 1976 with total page 276 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 704 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Study of Three-Dimensional Shock Wave Turbulent Boundary Layer Interaction - Scaling of Sharp and Blunt Fin-Induced Flowfields by : David S. Dolling
Download or read book Experimental Study of Three-Dimensional Shock Wave Turbulent Boundary Layer Interaction - Scaling of Sharp and Blunt Fin-Induced Flowfields written by David S. Dolling and published by . This book was released on 1980 with total page 61 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental study of three-dimensional (3-D) shock wave turbulent boundary layer interaction has been carried out. Interactions generated by fin models having sharp and hemi-cylindrically blunted leading edges have been studied. Tests have been made using incoming turbulent boundary layer varying in thickness in the ratio of about 4:1. Extensive surface property measurements have been made on the test surface on which the incoming boundary layer developed and on the fin itself. All of these tests were carried out at a nominal freestream Mach number of 3, a freestream unit Reynolds number of about 63 million per meter, and under approximately adiabatic wall conditions. The emphasis in the study reported on in this paper was on two main areas. First, to determine the key geometric and/or flow parameters controlling the overall scaling and characteristics of both blunt and sharp fin-induced interactions. Second, to identify the conditions under which both blunt and sharp fins induced interactions have the same local scale and characteristics. (Author).
Book Synopsis Three-Dimensional Shock Wave and Turbulent Boundary Layer Interactions by : Seymour M. Bogdonoff
Download or read book Three-Dimensional Shock Wave and Turbulent Boundary Layer Interactions written by Seymour M. Bogdonoff and published by . This book was released on 1985 with total page 75 pages. Available in PDF, EPUB and Kindle. Book excerpt: An extensive experimental study of three-dimensional shock wave turbulent boundary layer interactions caused by shock generators defined solely by angles has been carried out at Mach 3. Sharp fins, sharp swept fins, swept wedges, and semi-cones have been used to generate a wide range of shock waves. The interaction of these waves with turbulent boundary layers has been investigated by surface flow visualization, mean surface static pressure distributions, flowfield surveys of total pressure and yaw, and several flowfield visualization techniques. Some exploratory high frequency surface pressure measurements have been carried out to evaluate the steadiness of these interactions. Scaling laws for both surface and flowfield features have been derived. Some limited studies were carried out at a Mach number of 2. A flowfield study has shown that the initial part of interactions caused by the same strength and geometrical shock wave generated by different shock generators are all similar. The 'footprints' of the interactions, as shown by surface flow visualization, can be categorized as approximately conical or cylindrical, and the boundaries between these two regions have been defined for both Mach 3 and Mach 2. There are still questions with regards to the detailed flowfield structures and physical mechanisms, but the three-dimensional interactions appeared to be less unsteady than that of two-dimensional separated flows.
Book Synopsis Shock Wave-Boundary-Layer Interactions by : Holger Babinsky
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.
Book Synopsis The Study of Shock Wave and Turbulent Boundary Layer Interactions by : Seymour M. Bogdonoff
Download or read book The Study of Shock Wave and Turbulent Boundary Layer Interactions written by Seymour M. Bogdonoff and published by . This book was released on 1986 with total page 43 pages. Available in PDF, EPUB and Kindle. Book excerpt: The three dimensional shock wave turbulent boundary layer interaction generated by several shock generators defined solely by angles has been carried out at a Mach number of 3. Interactions with thin boundary layers were used to obtain overall characteristics, while interactions with thick boundary layers permitted detailed high resolution surveys. Investigations of the interactions were carried out by mean and high frequency surface pressure distribution measurements, surface flow visualization, and mean total head, yaw, and static pressure distributions through the flowfield. Major new data sets were obtained for the interaction of the shock wave generated by a 20 deg fin, and by a 24 deg wedge swept at 60 deg to the incoming flow. A series of tests were carried out to examine new concepts of three-dimensional interactions and extensive 'non-steady' results were obtained from the high frequency surface pressure distributions. Close coordination of the experiments with major computational efforts, support new concepts of flow structure and physics for these complex interactions. Keywords: Three-dimensional shock wave interactions; Conical similarity; Scaling laws; Conical/cylindrical boundary; Unsteady flow; Non-steady characteristics; flow physics and modeling; Supersonic characteristics.
Book Synopsis Experimental Investigation of Three-Dimensional Shock Wave Turbulent Boundary Layer Interaction: An Exploratory Study of Blunt Fin-Induced Flows by : David S. Dolling
Download or read book Experimental Investigation of Three-Dimensional Shock Wave Turbulent Boundary Layer Interaction: An Exploratory Study of Blunt Fin-Induced Flows written by David S. Dolling and published by . This book was released on 1980 with total page 75 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental study of three-dimensional (3-D) shock wave turbulent boundary layer interaction has been carried out. Interactions generated by fin models having sharp and hemi-cylindrically blunted leading edges have been studied. The emphasis in this particular study was twofold. First, the influence of incoming turbulent boundary layer thickness delta on the streamwise, spanwise and vertical scaling of the interaction was examined. Turbulent boundary layers varying in thickness from .127 cm (.05 in.) to 2.27 cm (0.89 in.) were used. In addition, a study has been conducted to examine the effects of the ratio D/delta (where D is the blunt fin leading edge diameter) on the interaction properties and scaling. Second, an investigation has been started to examine the unsteady shock wave-boundary layer structure and the resulting high frequency, large amplitude pressure fluctuations which occur ahead of and around the blunt fin leading edge. This is an area which in the past has been largely ignored, yet has important implications, since it is not clear that any mean surface property or flowfield measurements have any real physical significant. To date, measurement techniques and computer software have been developed and exploratory measurements made in the undisturbed turbulent boundary layer and also on the plane of symmetry ahead of the blunt fin.
Book Synopsis Boundary Layer Effects by : Anthony W. Fiore
Download or read book Boundary Layer Effects written by Anthony W. Fiore and published by . This book was released on 1978 with total page 962 pages. Available in PDF, EPUB and Kindle. Book excerpt: In 1975 the U.S. Air Force and the Federal Republic of Germany signed a Data Exchange Agreement numbered AF-75-G-7440 entitled 'Viscous and Interacting Flow Fields.' The purpose was to exchange data in the area of boundary layer research. It includes both experimental and theoretical boundary layer research at speeds from subsonic to hypersonic Mach numbers in the presence of laminar, transitional, and turbulent boundary layers. The main effort in recent years has been on turbulent boundary layers, both attached and separated in the presence of such parameters as pressure gradients, wall temperature, surface roughness, etc. In the United States the research was conducted in various Department of Defense, NASA, aircraft corporations, and various university laboratories. In the Federal Republic of Germany it was carried out within the various DFVLR, industrial, and university research centers.
Book Synopsis A study of three-dimensional interaction flow fields between swept shock waves and turbulent boundary layers - flow structures and effects of bleed by : Masato Tamayama
Download or read book A study of three-dimensional interaction flow fields between swept shock waves and turbulent boundary layers - flow structures and effects of bleed written by Masato Tamayama and published by . This book was released on 1994 with total page 31 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Exploratory Study of a Three-Dimensional Shock Wave Boundary Layer Interaction at Mach 3 by : B. Oskam
Download or read book An Exploratory Study of a Three-Dimensional Shock Wave Boundary Layer Interaction at Mach 3 written by B. Oskam and published by . This book was released on 1975 with total page 15 pages. Available in PDF, EPUB and Kindle. Book excerpt: An exploratory experimental investigation has been carried out on the three dimensional flow fields caused by the interaction of oblique shock waves and a planar turbulent boundary layer. The study was performed at a free stream Mach number of 2.95, a Reynolds number per inch of 1.6 million and near adiabatic wall conditions. The interaction was studied on two experimental configurations having different initial boundary layer thicknesses (delta = approx. 0.13 and 0.55 inches). Both surface measurements as well as complete flow field surveys were performed. The main contributions of the present investigation are two experimentally derived flow field models for shock generator angles of 4 deg and 10 deg. Based upon both static pressure and surface flow patterns, as well as heat transfer data, the interaction region can be characterized as quasi-two-dimensional along the shock direction in the region studied. A critical examination of the occurrence of 'ordinary' flow separation and its character, as applied to the present problem, was carried out. It was concluded that McCabe's criterion, as used by the previous investigators, is not a sufficient condition to determine the onset of flow separation.
Book Synopsis Experiments on the Interaction with a Turbulent Boundary Layer of a Skewed Shock Wave of Variable Strength at Mach 2.5 by : L. Michael Freeman
Download or read book Experiments on the Interaction with a Turbulent Boundary Layer of a Skewed Shock Wave of Variable Strength at Mach 2.5 written by L. Michael Freeman and published by . This book was released on 1975 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report covers an experimental study of the interaction of a skewed shock wave of variable strength with a turbulent boundary layer at a working Mach number of 2.5. The skewed shock wave was generated by a vertical wedge whose angle was varied in increments of 1 degree or less between 6 and 18 degrees in order to cover the spectrum of interaction from below incipient to widespread separation. Measurements include pressure distributions and oil flow photographs. The incipient separation angle was found to be between 71/2 and 8 degrees. For large wedge angles there is the appearance in the oil flow photographs of an inflection within the separated region, suggesting the possible approach to a secondary separation. The extent of separation is relatively small for angles up to 10 degrees, but grows more rapidly for larger angles. (Author).
Book Synopsis Three-dimensional Interactions and Vortical Flows with Emphasis on High Speeds by : David J. Peake
Download or read book Three-dimensional Interactions and Vortical Flows with Emphasis on High Speeds written by David J. Peake and published by . This book was released on 1980 with total page 232 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Three-Dimensional Study of Fin-Induced Shock Wave Turbulent Boundary Layer Interaction by : D. S. Dolling
Download or read book A Three-Dimensional Study of Fin-Induced Shock Wave Turbulent Boundary Layer Interaction written by D. S. Dolling and published by . This book was released on 1977 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: Surface pressure distributions and oil streak patterns have been measured in the three-dimensional flowfield caused by the interaction of a skewed shock wave with a two-dimensional turbulent boundary layer. The boundary layer was developing on a 45 deg sweptback, sharp leading edged plate. Tests were made at a freestream Mach number of 2.95, a freestream unit Reynolds number of 63,000,000/m (1,600,000/in), a stagnation temperature of about 265 K and at near adiabatic wall temperature. Measurements have been made for generator angles in the range 0 to 12 deg in 2 deg increments. These measurements represent the first phase of a study which will include heat transfer measurements and details of the flowfield. The measured data are presented and compared with data obtained under the same shock wave conditions but with a different boundary layer. (Author).
Book Synopsis Shock Wave-turbulent Boundary Layer Interaction in a Three-dimensional Flow by : D. Barberis
Download or read book Shock Wave-turbulent Boundary Layer Interaction in a Three-dimensional Flow written by D. Barberis and published by . This book was released on 1995 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Three-Dimensional Flowfield in a Swept Shock Wave/Boundary-Layer Interaction and Its Response to Pulsed Microjet Actuation by : Lee J. Mears
Download or read book Three-Dimensional Flowfield in a Swept Shock Wave/Boundary-Layer Interaction and Its Response to Pulsed Microjet Actuation written by Lee J. Mears and published by . This book was released on 2020 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Research efforts in shock wave/boundary-layer interactions (SBLI) are motivated by the pursuit of faster, lighter, and more maneuverable aircraft. Flow separation, strong pressure fluctuations, and high aerodynamic heating are all detrimental phenomena associated with these interactions. With a deeper understanding of the physics that drive the inherent unsteady pressure and shear forces, engineers can apply control techniques that target important flow regions and frequencies instead of overdesigning vehicles to survive these adverse effects. However, the mechanisms that drive the unsteady behavior in SBLI have been difficult to isolate and accurate predictions of unsteady pressure are not currently achievable for simulations with realistic Reynolds numbers. In order to further the understanding of 3-D SBLI physics, an experimental investigation of controlled perturbations introduced to a fin-generated swept shock wave/boundary-layer interaction is conducted. The principal mean and unsteady flow features are studied with special emphasis on the difference between separation found in two-dimensional and three-dimensional interactions. Regions of high-amplitude pressure fluctuation on the surface beneath the interaction and coincident unsteady flow features above the surface are identified to support the development of physics-based models of interaction unsteadiness. Several techniques are employed to measure the flow response, including steady and unsteady surface pressure measurements using pressure-sensitive paint (PSP), shadowgraph to capture shock motion, particle image velocimetry (PIV) to quantify velocity fields in the flow, and high-bandwidth unsteady pressure sensors. Global measurement techniques, including steady and unsteady PSP, tomographic PIV, and multiple planes of high-speed stereo PIV permit uniquely illuminating analysis of the flow dynamics. Some of the experimental methods are novel for the facilities and types of flows, and validation and uncertainty quantification efforts are included. Controlled flow perturbations, which have been historically difficult to implement in supersonic flows due to strong momentum of the flow and limited bandwidth of available actuators, are introduced within the interaction to gauge flow response to frequency and location of the disturbance. The perturbations are generated from Resonance-Enhanced Microjets (REM) which produce pulsed supersonic jets at frequencies on the order of several kilohertz. An evolution in the design of surface-mounted, modular REM actuators produces an improved implementation with greater repeatability and bandwidth. The frequency range studied here (between 2 and 4 kHz) has been selected based on separation and reattachment dynamics measured by unsteady pressure on the surface beneath the interaction. Measurements combining the plate and heretofore-unstudied fin surface provide significantly more information about the response of this complex, highly three-dimensional interaction with details that are not easily obtained using traditional sensors. In general, the disturbances created by the actuators were found to excite convective mechanisms within the interactions and remained localized. Large-scale alterations in the flowfield due to microjet blowing are noted, including reduction of the size of separation and smaller shock traverse distances. The flow response to pulsed actuation reveals varying sensitivity of interaction key features, which offers promise for future efforts to design more effective flow control devices.
