Change in the shape of the diffracting shock wave at a convex corner

Баженова, Т. В.; Gvozdeva, L. G.; Zhilin, Yu. V.

doi:10.1016/b978-0-08-025442-5.50039-1

Cited by 10 publications

(13 citation statements)

References 7 publications

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“…There have been a variety of experimental studies, ineluding Skews (1967aSkews ( , 1967b, Glass (1967), Bazhenova et al (1971Bazhenova et al ( ,1973, Bazhenova et al (1979), Matsuo et al Offprint requests to: R. HiUier (1990) and an extensive review by Bazhenova et al (1984). Several important features can be noted from these and we confine our observations here to sufficiently strong incident shock waves that the initial post-shock flow is supersonic.…”

Section: Introductionsupporting

confidence: 51%

“…Fig. 9a includes the computational estimates of the velocity (.0 or ~) of this tertiary shock wave at the wall, showing good agreement with the specific data point taken from flow visualization pictures in Bazhenova et al (1979).…”

Section: Diffraction Resultsmentioning

confidence: 72%

“…At the lowest Mach number it is naturally weak and stands well clear of the wall; at the highest Mach number only a vestige of it remains, presumably associated with the relative weakening of the vortex and the role of the Math shock system in reducing the need for further strong compression to decelerate the reverse flowing gas. Although Skews makes no mention of a tertiary wave system, it has been clearly identified by others, including Bazhenova et al (1979Bazhenova et al ( , 1984, Matsuo et al (1990) and Gvozdeva and Lyakhov (1988) for a comparable range of incident shock Mach number. Fig.…”

Section: Diffraction Resultsmentioning

confidence: 92%

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Computation of shock wave diffraction at a ninety degrees convex edge

Hillier

1991

Shock Waves

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Abstract. This paper presents a numerical study of shock wave diffraction at a sharp ninety degrees edge, using an explicit second-order Godunov-type Euler scheme based upon the solution of a generalized Riemann problem (GRP). The Euler computations produce flow separation very close to the diffraction edge, leading to a realistic development of the separated shear layer and subsequent vortex roll-up. The diffracted shock wave, and the secondary shock wave, are both reproduced well. In addition a pair of vortex shocks are shown to form, extending well into the vortex core.

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Section: Introductionsupporting

confidence: 51%

Section: Diffraction Resultsmentioning

confidence: 72%

Section: Diffraction Resultsmentioning

confidence: 92%

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Computation of shock wave diffraction at a ninety degrees convex edge

Hillier

1991

Shock Waves

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“…Several experimental results for shock diffraction over a convex corner have been published, for example [1,2,16,21]. Similarly, numerical results are in abundance, for example [3,6,7,13,[18][19][20][22][23][24].…”

Section: Shock Diffraction Over a Cornermentioning

confidence: 98%

Numerical simulation of shock diffraction on unstructured meshes

2006

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“…The formation of a spiral vortex from the diffraction of a shock wave over a convex corner has been extensively studied [1][2][3][4][5]. The flow features that characterise the shock wave diffraction without co-flow have been analysed with incident shock Mach numbers in the range of 1.0 to 5.0 [6].…”

Section: Introductionmentioning

confidence: 99%

Shock wave diffraction in the presence of a supersonic co-flow jet

Gnani

Zare‐Behtash

et al. 2016

Shock Waves

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The interaction between a diffracting shock wave and a uniform jet is a case that so far has only been partially investigated. This interaction is extremely important for the control of noise generation and improvement of combustor performance. To fill this knowledge gap, three geometries of the diffracting corner, namely a straight ramp, a serrated ramp, and a rounded corner, have been tested experimentally to study the interaction of shock diffraction with a supersonic co-flow jet at incident Mach numbers of 1.31 and 1.59, with Reynolds numbers of 1.08 × 10 6 and 1.68 × 10 6 , respectively. Schlieren photography was employed to analyse the evolution of the flow phenomena. The aim is to provide a qualitative understanding of the interaction between the diffracting shock wave and the uniform jet relevant to future high-speed transport. The results show that the flow field evolves more rapidly and develops stronger structures for a higher shock Mach number. The diffraction around a rounded splitter develops a periodical vortical structure which continues after the disturbance introduced by the passage of the shock wave is removed.Keywords Shock wave diffraction · Vortex · Schlieren · Unsteadiness 1 Nomenclature ASCurved acoustic wave CS Contact surface CF SL Co-flow shear layer

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Change in the shape of the diffracting shock wave at a convex corner

Cited by 10 publications

References 7 publications

Computation of shock wave diffraction at a ninety degrees convex edge

Computation of shock wave diffraction at a ninety degrees convex edge

Numerical simulation of shock diffraction on unstructured meshes

Shock wave diffraction in the presence of a supersonic co-flow jet

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