On the shock-on-shock interaction problem

Kutler, Paul; Sakell, Leonidas; Aiello, Gene

doi:10.2514/6.1974-524

Cited by 9 publications

(2 citation statements)

References 3 publications

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“…Merritt & Aronson (1966) and Merritt & Aronson (1967) studied the head-on interaction of a flying supersonic model of a hemisphere-cylinder, right circular cylinder, 60 • wedge and 9 • half-angle cone. Numerical simulations for shock-on-shock interaction are given by Kutler, Sakell & Aiello (1974 and , using a second-order, shock-capturing, finite-difference approach. Li & Ben-Dor (1997) presented a more general model based on two-and three-shock theories and classified shock-on-shock interaction into regular and irregular interactions.…”

Section: Introductionmentioning

confidence: 99%

Reflection of a rightward-moving oblique shock of first family over a steady oblique shock wave

Wang,

Xu,

2024

J. Fluid Mech.

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The reflection of a rightward-moving oblique shock (RMOS) belonging to the first family, over an initially steady oblique shock wave (SOSW) produced by a wedge, is studied in this paper. To cover all possibilities, the problem is divided into a pre-shock reflection problem, for which the incident shock is assumed to reflect over the pre-interaction part of the SOSW, and a post-shock reflection problem, for which the incident shock is assumed to reflect over the post-interaction part. Such division, together with the definition of the equivalent problem defined on the reference frame co-moving with the nominal intersection point of the two shock waves, allows us to connect the reflection patterns with the six types of shock interference of Edney, which include type I–VI shock interferences depending on how an upstream oblique shock intersects a bow shock (types I and II are regular and Mach reflections of two shocks from the opposite sides; type III and type IV have two triple points or two Mach reflection configuration; type V and type VI are irregular and regular reflections of two shocks from the same side). We are thus able to identify all possible shock reflection types and find their transition conditions. Pre-shock reflection may yield IV, V and VI (of Edney's six types) shock interferences and post-shock reflection may yield I, II and III shock interferences. Pre- and post-shock reflections possibly occur at two different parts of the SOSW, and the complete reflection configuration may have one or both of them. Both transition condition study and numerical simulation are used to show how pre-shock reflection and post-shock reflection exist alone or coexist, leading to various types of combined pre-shock and post-shock reflections.

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Section: Introductionmentioning

confidence: 99%

Reflection of a rightward-moving oblique shock of first family over a steady oblique shock wave

Wang,

Xu,

2024

J. Fluid Mech.

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“…6 ' 9 ' 14 This paper does not try to summarize them by commenting on the relative merits or shortcomings of each, rather the reader is referred to papers by Aiello, 15 and Kutler et al 9 for brief summaries of some of the existing theories. In general, most of the early theories required assumptions regarding the position and structure of the existing shock waves for their model.…”

Section: Introductionmentioning

confidence: 98%

Three-Dimensional, Shock-on-Shock Interaction Problem

Kutler

Sakell

1975

AIAA Journal

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The unsteady, three-dimensional flowfield resulting from the interaction of a plane shock with a cone-shaped vehicle traveling supersonically is determined using a second-order, shock-capturing, finite-difference approach. The time-dependent, inviscid gas dynamic equations are transformed to include the self-similar property of the flow, to align various coordinate surfaces with known shock waves, and to cluster points in the vicinity of the intersection of the transmitted incident shock and the surface of the vehicle. The governing partial differential equations in conservation-law form are then solved iteratively using MacCormack's algorithm. The computer simulation of this problem, compared with its experimental counterpart, is relatively easy to model and results in a complete description of the flowfield including the peak surface pressure. The numerical solution, with its complicated wave structure, compares favorably with the available schlieren photographs, and the predicted peak surface pressures obtained are shown to agree better with the experimental data than existing approximate theories.

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Computation of three-dimensional, inviscid supersonic flows

Kutler

Progress in Numerical Fluid Dynamics

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On the shock-on-shock interaction problem

Cited by 9 publications

References 3 publications

Reflection of a rightward-moving oblique shock of first family over a steady oblique shock wave

Reflection of a rightward-moving oblique shock of first family over a steady oblique shock wave

Three-Dimensional, Shock-on-Shock Interaction Problem

Computation of three-dimensional, inviscid supersonic flows

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