A CFD study of precombustion shock-trains from Mach 3-6

Hinter, L.; Couch, B D

doi:10.2514/6.1990-2220

Cited by 8 publications

(2 citation statements)

References 5 publications

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“…However, experimental and analytical work by Waltrup & Billig (1973) gave useful descriptions of the pseudo-shock geometry and characteristics, and this eventually led to optimal dual-mode engine designs (Billig & Sullins 1993). Important contributions to the understanding of isolator behavior were made through CFD (Hunter & Couch 1990;Lin et a1 1991a,b;Sullins & McLafferty 1992;Elmquist 1993). Significant advances in understanding pseudo-shocks were made by FSU authors, particularly the pioneering works of Ostras & Penzin (1977) and Penzin (1989).…”

mentioning

confidence: 99%

Fluid Phenomena in Scramjet Combustion Systems

Curran¹,

Heiser²,

Pratt³

1996

Annu. Rev. Fluid Mech.

238

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This paper reviews important advances in understanding and predicting the behavior of scramjet combustion systems since the classic article published in this series by Antonio F e d (1973). The review focuses on basic fluid phenomena and is divided into three distinct sections. The first briefly describes progress that has been made in the design and demonstration of practical scramjets around the world, especially in the US, the FSU, France, and Germany. The second provides a contemporary exposition of the aerothermodynamics of the dual-mode ramjetkcramjet combustion system, accounting for the role of the isolator in preventing unstart from either thermal choking or flow separation due to heat release. The third part summarizes the current state of knowledge regarding fuelair mixing in dual-mode ramjetkcramjet combustors, especially the potential of axial vorticity to increase mixing effectiveness over that of lateral vorticity. 'The US Government has the right to retain a nonexclusive, royalty-free license in and to any 323 copyright covering this paper.

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mentioning

confidence: 99%

Fluid Phenomena in Scramjet Combustion Systems

Curran¹,

Heiser²,

Pratt³

1996

Annu. Rev. Fluid Mech.

238

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“…Computational simulations of shocktrain and pseudo-shock-dominated flows have proven difficult and non-predictive. 20,21 As an alternative, simplified models of shock-train and pseudo-shock evolution have been proposed, all of which share the following characteristics: provide a basis for decomposing shock-trains into simple, well-known unit processes, 15 for example: (a) oblique shocks formed by virtual compression corners, (b) subsonic-supersonic acceleration through virtual converging-diverging flow areas, (c) flow through normal shocks, and (d) shock reflection at shock-intersection points.…”

Section: Qualitative Model Of Millisecond-scale Shock-boundary Layer/recirculation Zone Interactionmentioning

confidence: 99%

Millisecond-scale shock-train evolution in high-pressure ratio nozzles: Schlieren imaging and qualitative analysis of shock–boundary layer interaction

Keanini

Tkacik

Srivastava

et al. 2013

Proceedings of the Institution of Mechanical Engineers, Part G:

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The classical picture of shock evolution in nozzles holds that under over-expanded flow conditions, a single, nominally normal shock exists within the nozzle. Focusing on the highly dynamic flow produced during blow-down of an experimental, high-nozzle pressure ratio, planar nozzle, this article presents visual evidence that shock-trains – here, a pair of parallel, nominally normal shocks – dominate the rapidly evolving flow field. Three principal results are presented in this study. First, high-speed schlieren images of the evolving nozzle flow are reported. Second, a simple qualitative model of shock–boundary layer/recirculation zone interaction is proposed and used to explain observed millisecond-scale shock-train structure. Third, limited wall pressure measurements and schlieren images are combined to propose a second qualitative model of shock-train–boundary layer/recirculation zone evolution on the longer blow-down process time-scale. The results provide insight into millisecond-scale compressible flow dynamics within high-nozzle pressure ratios .

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