Comparison of numerical oblique detonation solutions with an asymptotic benchmark

Grismer, Matthew J.; Powers, Joseph M.

doi:10.2514/3.11653

Cited by 9 publications

(8 citation statements)

References 3 publications

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“…In an effort to better relate these models to propulsion applications, Powers and Gonthier, 1992b, give a methodology to study of the configuration of Figure 7 along with a simple, non-rigorous anal- Grismer and Powers, 1992. ysis. The analysis divides the flow into six zones: 1) a pre-shocked region, 2) a post-shocked region, 3) a Prandtl-Meyer rarefaction region, 4) a post-rarefaction region, 5) a post-flame sheet region, and 6) a post-shock region.…”

Section: Summary Of Resultsmentioning

confidence: 99%

“…Recent analyses which this author and colleagues have performed have placed emphasis on oblique detonations with resolved reaction zone structure and the connections of these structures with the predictions of a RH analysis: (Powers and Stewart, 1992), (Powers and Gonthier, 1992a), and (Grismer and Powers, 1992). In addition, there is a new large body of general unsteady analyses of one-and two-dimensional detonations which though germane, have largely not been applied in propulsion studies, e.g.…”

Section: Reviewmentioning

confidence: 99%

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Oblique Detonations: Theory and Propulsion Applications

Powers

1994

ICASE/LaRC Interdisciplinary Series in Science and Engineering

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The oblique detonation, a combustion process initiated by an oblique shock, arises in most supersonic combustion applications including, most notably, the ram accelerator and the oblique detonation wave engine. Additionally, it is the generic two-dimensional compressible shocked reacting flow; consequently, its basic research value is inherent. The outstanding theoretical questions are also the fundamental practical questions: e.g. what conditions are necessary for steady solutions, what is the dependency of the steady propagation speed on the ambient condition, what is the susceptibility of the system to instability, and what is the behavior of the system in unsteady operation. A related topic which transcends all questions is the ability to describe these phenomena computationally. At this early stage, these issues are most clearly addressed with simple models. This paper will review the application of such models to oblique detonations and discuss their future relevance.

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Section: Summary Of Resultsmentioning

confidence: 99%

Section: Reviewmentioning

confidence: 99%

Oblique Detonations: Theory and Propulsion Applications

Powers

1994

ICASE/LaRC Interdisciplinary Series in Science and Engineering

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“…In the work by Powers and Stewart, two solutions were presented: a straight wedge supporting a curved shock and a curved wedge supporting a straight shock. Grismer and Powers [26] used the straight wedge, curved shock solution to compare a numerical solution algorithm to the analytical solution. Grismer and Powers intent was to demonstrate the use of these analytical solutions as an aid to code development.…”

Section: Oblique Detonation Wavementioning

confidence: 99%

About the formulation, verification and validation of the hypersonic flow solver Eilmer

Gollan

Jacobs

2013

Numerical Methods in Fluids

143

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SUMMARYWe describe the formulation of the gas dynamics and high‐temperature thermochemical modules of the Eilmer code, an open‐source Navier–Stokes solver for transient compressible flow in two and three dimensions. The core gas dynamics formulation is based on finite‐volume cells, and the thermochemical effects are handled with specialised updating schemes that are coupled into the overall time‐stepping scheme. Verification of the code is explored via a number of case studies that use analytic and semi‐analytic solutions as comparison. These include both smooth and shocked flows and are used to demonstrate the order of spatial accuracy of the code. Cases include manufactured solutions for rather abstract inviscid and viscous flow, an idealised detonation wave supported by a curved body, and the transient flow of an idealised but high‐performance shock tube. Validation of the inviscid gas dynamics and thermochemical models is then explored using data from a selection of experimental studies. These studies include ballistic range experiments with chemically‐inert noble gases and high‐temperature chemically‐reacting air. These comparisons show that the code performs well and they provide a lesson in considering a range of experimental data rather than relying upon isolated data points for validation. These verification and validation cases are described in full detail and will be useful for other code developers of high‐temperature compressible flow solvers. Copyright © 2013 John Wiley & Sons, Ltd.

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“…Recent analyses which this author and colleagues have performed have placed emphasis on oblique detonations with resolvpd reaction zone structure and the connections of these structures with the predictions of a RH analysis: , Powprs and Gonthier (1992a), and Grismer and Powers (1992). In addition, there is a new large body of general unsteady analyses of one-and twodimensional detonations which though germane, have largely not been applied in propulsion studies, e.g.…”

Section: Reviewmentioning

confidence: 99%

“…Figure 11: DinH'nsionless pressure contours predicted by asymptotic and numerical analysis, from Grismer and Powers (1992). Though they cannot serve as a substitute for either comprehensive models or experiments (both of which have their difficulties), they can be useful guides for understanding.…”

Section: Recommendationsmentioning

confidence: 99%

Combustion in High-Speed Flows

Buckmaster¹,

Jackson²,

Kumar³

1994

ICASE/LaRC Interdisciplinary Series in Science and Engineering

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The focus of the second workshop was directed towards the development, analysis, and application of basic models in high speed propulsion of particular interest to NASA. The exploration of a dual approach combining asymptotic and numerical methods for the analysis of the models was particularly encouraged. The objectives of this workshop were i) the genesis of models that would capture or reflect the basic pllysical phenomena in SCRAMJETs and/or oblique detonation-wave engines (ODWE), and ii) the stimulation of a greater interaction between NASA experimental research community and the academic community.The lead paper by D. Bushnell on the status and issues of high speed propulsion relevant to both the SCRAMJET and the ODWE parallels his keynote address which set the stage of the workshop. Following the lead paper were five technical sessions with titles and chairs: Experiments (C. Rogers), Reacting Free Shear Layers (C. E. Grosch), Detonations (A. K. Kapila), Ignition and Structure (J. Buckmaster), and Unsteady Behaviour ('1'. L. Jackson).The session chairs were responsible for the planning of their session. In each of the sessions formal discussion papers were given by experts followed by a general discussion involving the participants. This volume contains the manuscripts presented in each session. In addition, a panel discussion was held on the last day, chaired by J. Buckmaster. The panel members were

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Comparison of numerical oblique detonation solutions with an asymptotic benchmark

Cited by 9 publications

References 3 publications

Oblique Detonations: Theory and Propulsion Applications

Oblique Detonations: Theory and Propulsion Applications

About the formulation, verification and validation of the hypersonic flow solver Eilmer

Combustion in High-Speed Flows

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