Topic
Oblique shock
About: Oblique shock is a research topic. Over the lifetime, 6551 publications have been published within this topic receiving 119823 citations.
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TL;DR: In this article, numerical simulations using Euler equations with detailed chemistry are performed to investigate the effect of fuel-air composition inhomogeneity on the oblique detonation wave (ODW) initiation in hydrogen-air mixtures.
62 citations
01 Jan 1995
TL;DR: In this paper, a model aimed at determining the boundaries of the possible interaction regimes for an ideal dissociating gas is presented. But the effects of dissociative relaxation processes on cold hypersonic flow are unknown.
Abstract: The impingement of shock waves on blunt bodies in steady supersonic flow is known to cause extremely high local heat transfer rates and surface pressures. Although these problems have been studied in cold hypersonic flow, the effects of dissociative relaxation processes are unknown. In this paper we report a model aimed at determining the boundaries of the possible interaction regimes for an ideal dissociating gas. Local analysis about shock wave intersection points in the pressure-flow deflection angle plane with continuation of singular solutions is the fundamental tool employed. Further, we discuss an experimental investigation of the nominally two-dimensional mean flow that results from the impingement of an oblique shock wave on the leading edge of a cylinder. The effects of variations in shock impingement geometry were visualized using differential interferometry. Generally, real gas effects are seen to increase the range of shock impingement points for which enhanced heating occurs. They also reduce the type IV (Edney 1968 a,b) interaction supersonic jet width and influence the type II—III transition process.
62 citations
TL;DR: In this paper, the authors examined the fundamental mechanism of broadband shock noise in an improperly expanded supersonic jet, including circular convergent and convergent-divergent nozzles, and determined the main source of shock noise is the transient interaction between the shock front and the convected vorticity within the jet plume.
Abstract: This paper examines the fundamental mechanism of broadband shock noise in an improperly expanded supersonic jet. The study includes circular convergent and convergent-divergent nozzles. The main source of shock noise is determined to be the transient interaction between the shock front and the convected vorticity within the jet plume. The discussion of the noise generation mechanism is based on detailed numerical analysis, theoretical modeling, refined measurements of the jet mean flow, shock-cell structure, turbulence, and noise. Results in this study provide a broad-based generalization for the Harper-Bourne and Fisher analysis and prediction method.
62 citations
TL;DR: Oblique shock detection in conical nozzle with circular arcs throat with circular arc throat is studied, noting measurement techniques.
Abstract: Oblique shock detection in conical nozzle with circular arc throat, noting measurement techniques
62 citations
62 citations