3 edition of Hypersonic shock/boundary-layer interaction database found in the catalog.
Hypersonic shock/boundary-layer interaction database
by National Aeronautics and Space Administration, Ames Research Center, For sale by the National Technical Information Service in Moffett Field, Calif, [Springfield, Va
Written in English
|Statement||Gary S. Settles and Lori J. Dodson.|
|Series||NASA contractor report -- 177577., NASA contractor report -- NASA CR-177577.|
|Contributions||Dodson, Lori J., United States. National Aeronautics and Space Administration.|
|The Physical Object|
In order to achieve proficient combustion with the present technologies, the flow through an aircraft intake operating at supersonic and hypersonic Mach numbers must be decelerated to a low-subsonic level before entering the combustion chamber. High-speed intakes are generally designed to act as a flow compressor even in the absence of mechanical compressors. The reduction in flow velocity is Author: Humrutha Gunasekaran, Thillaikumar Thangaraj, Tamal Jana, Mrinal Kaushik. shock/shock interactions -- shock/boundary-layer interactions -- shock wave reflections and diffractions -- shock wave propagation in condensed and heterogeneous materials -- dynamics of explosion and blast waves -- compressible multi-phase flows -- nozzles and jets -- transonic, supersonic and hypersonic flows -- shock focusing.
Analysis of Buzz in a Supersonic Inlet Rodrick V. Chima National Aeronautics and Space Administration Glenn Research Center Cleveland, Ohio Abstract A dual-stream, low-boom supersonic inlet designed for use on a small, Mach aircraft was tested. The ISSW31 focused on the following areas: Blast waves, chemical reacting flows, chemical kinetics, detonation and combustion, ignition, facilities, diagnostics, flow visualization, spectroscopy, numerical methods, shock waves in rarefied flows, shock waves in dense gases, shock waves in liquids, shock waves in solids, impact and compaction.
Great efforts have been dedicated during the last decades to the research and development of hypersonic aircrafts that can fly at several times the speed of sound. These aerospace vehicles have revolutionary applications in national security as advanced hypersonic weapons, in space exploration as reusable stages for access to low Earth orbit, and in commercial aviation as fast long-range Cited by: Welcome to The University of Arizona’s Research Catalog, an instance of Elsevier’s Pure Experts. The Research Catalog allows you to search for experts by navigating the hierarchy below, by concept or last name using the search box, or by free text inputs such as articles or funding opportunity announcements.
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The present report represents the result of the third and final phase: namely, recent additions and corrections to the hypersonic shock wave / turbulent boundary-layer interaction database. Get this from a library. Hypersonic shock/boundary-layer interaction database. [G S Settles; Lori J Dodson; United States.
National Aeronautics and Space Administration.]. The backup document for this paper (Settles, G. S., and Dodson, L. J., "Hypersonic Shock/Boundary- Layer Interaction Database," NASA CRApril ) contains these data in both tabulated. The shock wave boundary layer interaction in Fig.
4(a)–(b) was created by a shock generated by a 4 ∘ wedge. The boundary layer in Fig. 4(a) is laminar throughout the interaction. The incident shock, growth of the boundary layer in the neighborhood of the shock boundary layer interaction, and subsequent reflected shock are by: 6.
 to these hypersonic shock/boundary-layer interactions ﬂows. Based on past experience, the shock-unsteadiness correction is expectedto enhance ﬂowseparation at thecone–ﬂare junction. This will result in a better matching of the ﬂow topology and the shock structure in the interaction region with those observed in the experi-ments.
NASA-CR, a database report on hypersonic shock wave / turbulent boundary-layer interactions, was the product of phase 1 of that effort. Phase 2 produced a similar database, NASA-CR, covering the topics of attached hypersonic boundary layers in pressure gradients and compressible turbulent mixing layers.
The situation regarding the experimental database is, however, not particularly rosy. A recent compilation 3 has revealed that although there is a large number of hypersonic shock boundary-layer experiments, the quality of these experiments is varied.
A set of stringent criteria reduced candidate hypersonic studies to only Size: 2MB. This article presents an investigation on a correlation relevant to flow separation during shock wave–boundary layer interaction in a hypersonic flow. The study includes experimental as well as numerical components.
The hypersonic shock–boundary layer interactions were visualized to gauge the extent of flow separation on a flat plate on external shock by: 3. of Maryland at College Park, Adam Grumet and Charles Bollaro [2, 3] conducted research on hypersonic boundary layer-shockwave interaction utilizing the MacCormack Technique with certain freestream conditions.
The MacCormack Technique is the technique utilized in. shock/boundary layer interactions occur when shocks impinge on the sidewall of the tunnel. The shocks originate from the sting support or from models placed in the tunnel. These shocks disturb the boundary layer and can separate the flow far upstream.
These kinds of shock/boundary layer interactions are an important problem for hypersonic vehicles. The first case was a steady two‐dimensional shock/boundary layer interaction on a flat plate with a mixture of N2 and O2 in the freestream. It was found that the real gas effects reduce the size of the shock induced separation bubble and the magnitude of the surface heating by: Hypersonic shock-wave laminar boundary-layer interaction Delery  has shown that the upstream influence, a measure of the intensity of shock-wave boundary-layer interaction, increases with the ramp angle for fixed Mach and Reynolds numbers, and decreases with the Mach number for fixed ramp angle and Reynolds number; the separation length Cited by: A combined theoretical and experimental study is presented for the interaction between crossing shock waves generated by (10°, 10°) sharp fins and a flat plate turbulent boundary layer at Mach The theoretical model is the full 3-D mean compressible Reynolds-averaged Navier-Stokes RANS) equations incorporating the algebraic turbulent eddy viscosity model of Baldwin and by: Hypersonic flow over a double wedge configuration at continuum-like free stream conditions has been a challenging problem because of the multiple shock-shock and shock-boundary layer interaction, separated flows near the hinge, sheer layer, and three-dimensional effects.
These conditions generate a. This is the ﬁrst book devoted solely to a comprehensive state-of-the-art explanation 6 Experimental Studies of Shock Wave–Boundary-Layer Interactions in Hypersonic Flows 9 Shock-Wave Unsteadiness in Turbulent Shock Boundary-Layer Interactions.
Correlative behaviours of shock/boundary layer interaction induced by sharp fin and semicone. XUE-YING DENG; An experimental study of a three-dimensional shock wave/turbulent boundary-layer interaction at a hypersonic Mach number.
Hypersonic shock/boundary-layer interaction database. Mach 5 Shock Wave Boundary Layer Interaction: Study #1 Case Files. The following tar file is a complete package of grids, solutions, pre- and post-processing scripts, and experimental data used during the course of this validation study.
Download the tar file and extract the folder to see the files.  Séror S., Wexler J., Rubin T. and Kosarev L., “ Proposal of Low Cost Effective Building of a Database for Trip Induced Hypersonic Boundary Layer Implants on Hypersonic Wind-Tunnel Models,” Book of Abstracts of the 52nd Israel Annual Conference on Aerospace Sciences, Technion—Israel Inst.
of Technology, Haifa, Israel, Feb.–March Cited by: 2. The present database collection and assessment effort, with respect to shock/boundary layer interactions, include both supersonic (M 3 and above) and hypersonic data, both two-dimensional (2-D) and three-dimensional (3-D) data, and both unseparated and separated turbulent boundary layer cases (though the emphasis is on the latter).
Viscous interaction is one of the major aspects of hypersonic flows. Interaction between a shock wave and a boundary layer can produce a region of separated flow. The phenomenon may occur, for example, at the upstream-facing corner formed by deflected control surface on a hypersonic reentry vehicle, where the length of separation has.
Settles G S, Dodson L J. Hypersonic turbulent boundary-layer and free shear database. NASA-CR Settles G S, Dodson L J. Hypersonic shock/boundary-layer interaction database. New and Corrected Data.
NASA-CR Settles G S, Dodson L J. Supersonic and hypersonic shock boundary-layer interaction database.The flow field in a hypersonic inlet model at a design point of M = 6 has been studied experimentally. The focus of the current study is to present the time-resolved flow characteristics of separation shock around the cowl and the correlation between the separation shock oscillation induced by the unstart flow and the wall pressure fluctuation when the inlet is in a state of unstart.
High Author: Chengpeng Wang, Xin Yang, Longsheng Xue, Konstantinos Kontis, Yun Jiao. The challenges in understanding hypersonic flight are discussed and critical hypersonic aerothermodynamics issues are reviewed.
The ability of current analytical methods, numerical methods, ground testing capabilities, and flight testing approaches to predict hypersonic flow are evaluated.
The areas where aerothermodynamic shortcomings restrict our ability to design and analyze hypersonic Cited by: