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  • About
  • The Global ETD Search service is a free service for researchers to find electronic theses and dissertations. This service is provided by the Networked Digital Library of Theses and Dissertations.
    Our metadata is collected from universities around the world. If you manage a university/consortium/country archive and want to be added, details can be found on the NDLTD website.
1

Numerical solutions of internal and external hypersonic flows at high incidence.

Camerero, Ricardo. January 1973 (has links)
No description available.
2

Measurement of ablation in transient hypersonic flows /

Hunt, Dillon C. January 2001 (has links) (PDF)
Thesis (M.E. Sc.)--University of Queensland, 2002. / Includes bibliographical references.
3

AN INVESTIGATION OF THE INFLUENCE OF A FORWARD EJECTED GAS STREAM IN HYPERSONIC FLOW ABOUT BLUNT-BODIES

Tolle, Frederick Francis, 1921- January 1973 (has links)
No description available.
4

Numerical solutions of internal and external hypersonic flows at high incidence.

Camerero, Ricardo. January 1973 (has links)
No description available.
5

Shock-Wave / Boundary-Layer Interaction in Flow Over the High-Speed Army Reference Vehicle

Matthew Christophe Dean (16642239) 25 July 2023 (has links)
<p>Hypersonic flow over two generic missile configurations was investigated using CFD meth-</p> <p>ods. CFD results were compared with experimental results obtained by the hypersonic flight</p> <p>lab at Texas A&M University. Baseline RANS computations involving the missile configurations at a zero deg angle-of-attack were performed, along with computations at higher angles-of-attack. As the angle-of-attack was increased, complex vortex interactions were observed in the region between the fins. Increasing the angle-of-attack generally increased heating on the windward side of the missile geometries, especially on wall surface regions</p> <p>adjacent to the fin-root vortices. The results presented highlight observed fin region vortices and regions of intense heating on the body surface. DES simulations methods were also used to explore unsteady aspects of flow around the two generic missile configurations through time-accurate CFD simulations. Power spectral plots were generated to quantify the dominant frequencies of large-scale unsteadiness.</p>
6

Hypersonic aerospace vehicle leading edge cooling using heat pipe, transpiration and film cooling techniques

Modlin, James Michael 08 1900 (has links)
No description available.
7

Numerical study of energy utilization in nozzle/plume flow-fields of high-speed air-breathing vehicles

Wilson, Althea Grace, January 2008 (has links) (PDF)
Thesis (M.S.)--Missouri University of Science and Technology, 2008. / Vita. The entire thesis text is included in file. Title from title screen of thesis/dissertation PDF file (viewed April 25, 2008) Includes bibliographical references (p. 57).
8

Tomographic reconstruction of shock layer flows

Faletic, Rado, Rado.Faletic@anu.edu.au January 2005 (has links)
The tomographic reconstruction of hypersonic flows faces two challenges. Firstly, techniques used in the past, such as the Direct Fourier Method (DFM) or various backprojection techniques, have only been able to reconstruct areas of the flow which are upstream of any opaque objects, such as a model. Secondly, shock waves create sharp discontinuities in flow properties, which can be difficult to reconstruct both in position and in magnitude. This thesis will present a reconstruction method, utilising geometric ray-tracing and a sparse matrix iterative solver, which is capable of overcoming both of these challenges. It will be shown, through testing with phantom objects described in imaging and tomographic literature, that the results are comparable to those produced by the DFM technique. Finally, the method will be used to reconstruct three dimensional density fields from interferometric shock tunnel images, with good resolution.
9

Parallelized Cartesian Grid Methodology for Non-Equilibrium Hypersonic Flow Analysis of Ballutes

Lee, Jin Wook 09 July 2007 (has links)
Hypersonic flow analysis is performed on an inflatable aerocapture device called a "Ballute" for Titan's Mission. An existing unstructured Cartesian grid methodology is used as a starting point by taking advantage of its ability to automatically generate grids over any deformed shape of the flexible ballute. The major effort for this thesis work is focused on advancing the existing unstructured Cartesian grid methodology. This includes implementing thermochemical nonequilibrium capability and porting it to a parallel computing environment using a Space-Filling-Curve (SFC) based domain decomposition technique. The implemented two temperature thermochemical nonequilibrium solver governs the finite rate chemical reactions and vibrational relaxation in the high temperature regimes of hypersonic flow. In order to avoid the stiffness problem in the explicit chemical solver, a point implicit method is adopted to calculate the chemical reaction source term. The AUSMPW+ scheme with MUSCL data reconstruction is adopted as the numerical scheme to avoid non-physical oscillations and the carbuncle phenomenon. The results for five species air model and for thirteen species N2-CH4-Ar model to simulate Titan entry are included for verification against DPLR (NASA Ames' structured grid hypersonic flow solver). The efficient parallel computation of any unstructured grid flow solver requires an adequate grid decomposition strategy because of its complex spatial data structure. The difficulties of even and block-contiguous partitioning in frequently adapting unstructured Cartesian grids are overcome by implementing the 3D Hilbert SFC. Grids constructed by the SFC for parallel environment promise short inter-CPU communication time while maintaining perfect load balancing between CPUs. The load imbalance due to the local solution adaption is simply apportioned by re-segmenting the curve into even pieces. The detailed structure of the 3D Hilbert SFC and parallel computing efficiency results based on this grid partition method are also presented. Finally, a structural dynamics tool (LS-DYNA) is loosely coupled with the present parallel thermochemical nonequilibrium flow solver to obtain the deformed surface definition of the ballute.
10

Hyshot scramjet experiments in the T4 shock tunnel /

Frost, Myles Alexander. January 2001 (has links) (PDF)
Thesis (M. Eng. Sc.)--University of Queensland, 2002. / Includes bibliographical references.

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