Classification of shock wave reflections from a wedge. Part 1: Boundaries and domains of existence for different types of reflections

Семенов, А. Н.; Berezkina, M. K.; Krasovskaya, I. V.

doi:10.1134/s1063784209040082

Cited by 9 publications

(11 citation statements)

References 9 publications

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“…Triple Mach–White reflections (Semenov et al. 2009 a ) are characterized by the appearance of a new triple point that bifurcates the Mach stem; however, there is little data (Mach 2011) on its limits. The limits of Mach stem bifurcations are explored in this section as a function of , , and .…”

Section: Discussionmentioning

confidence: 99%

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Viscous jetting and Mach stem bifurcation in shock reflections: experiments and simulations

2020

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Section: Discussionmentioning

confidence: 99%

“…The vortex is large enough that it causes the slip line to deflect downwards. Double Mach reflections with a Mach stem bifurcation have been classified as triple Mach–White reflections by Semenov, Berezkina & Krasovskaya (2009 a ).…”

Section: Numerical Predictionmentioning

confidence: 99%

Viscous jetting and Mach stem bifurcation in shock reflections: experiments and simulations

2020

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“…The case of unsteady reflection from the wedge involves two simultaneous consistent processes: (i) reflection of shock wave and (ii) gas flow past the wedge behind the shock wave [9,10]. The reflected wave outgoing from the triple point converts into a wave at the wedge vertex.…”

Section: Formation Of Triple Shock Configurations With Negative Reflementioning

confidence: 99%

“…1a, with the reflected wave directed upward relative to the direction of motion of the inci dent flow, so that angle ω 2 in this configuration is pos itive. However, in a quasi steady case [4][5][6][7][8][9][10][11], both experiment and theory showed that the reflection of a shock wave from the planar wedge in a real gas leads to the appearance of more complex configurations, including those with a negative reflection angle (ω 2 < 0) whereby the shock wave near the triple point AR occurs below the line of incident flow. Figure 1b shows a schlieren photograph of the shock wave reflection in carbon dioxide [7] for a wave with the Mach number M = 5.18 incident on a wedge with angle α = 32° at an initial gas pressure of p 0 = 20 Torr.…”

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confidence: 97%

Formation of triple shock configurations with negative reflection angle in steady flows

Gvozdeva

Gavrenkov

2012

Tech. Phys. Lett.

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Triple shock wave configurations, together with two shock ones, play a determining role in all prob lems of both internal and external aerodynamics [1]. These shock wave configurations appear at the entrance of air inlets during supersonic flights (Fig. 1a), where incident wave IA at the wedge vertex cannot be reflected from the axis of symmetry in a reg ular manner. When a supersonic nozzle operates in an overexpanded mode a bridge like system of shock waves appears that represents a sequence of three shock configurations. In a quasi steady case, the reflection of a shock wave from a planar wedge with an angle below the critical value also leads to the appear ance of a Mach configuration (Fig. 1b). In this case, the triple point moves at a constant angle relative to the surface. Thus, in the system of reference related to the point A, we observe a steady state three shock config uration.The arrangement and intensities of shock waves in these configurations depend on the Mach number M 1 of the incident flow, initial angle of incidence ω 1 , and ratio of specific heats γ (adiabatic index). As is known, in the case of strong shock waves, these configurations can be calculated using a three shock theory [2, 3]. According to this, it is suggested that, in a certain vicin ity of the triple point where all waves are direct, each shock obeys the laws of conservation and the boundary conditions are as follows: (i) flow through the incident and reflected waves is parallel to flow through the Mach wave and (ii) pressures on both sides of the tangential discontinuity surface AT are the same. For strong shock waves, the three shock theory provides a quite satisfac tory agreement with experiment. However, it should be noted that this theory cannot determine the Mach stem height in a steady case and the angle of motion of the triple point in a quasi steady case.Abstract-Triple configurations of shock waves with negative reflection angles are considered. These config urations have been observed in quasi steady cases of shock wave reflection from a planar wedge in real gases, while in steady cases three shock configurations are only known to occur with positive reflection angles. Boundaries for the appearance of a three shock configuration with a negative reflection angle in steady cases are analytically determined as dependent on the initial Mach number of the flow, angle of incidence, and adi abatic index. The formation of a three shock configuration with a negative reflection angle in a steady flow must lead to a change in the character of the wave pattern, and under certain conditions it can lead to insta bility.

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“…1. The Mach reflection type can be further subdivided into different regimes of reflections which have recently been classified by Semenov et al [22,23] and Vasilev et al [24]. The isentropic exponent γ, the geometry (angle of the wall), and the Mach number of the incident shock M i = D/c 0 uniquely define the problem; the type of reflection is subject to change with any of those variables.…”

Section: Introductionmentioning

confidence: 99%

Non-uniqueness of solutions in asymptotically self-similar shock reflections

Lau-Chapdelaine

Radulescu

2013

Shock Waves

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The present study addresses the self-similar problem of unsteady shock reflection on an inclined wedge. The start-up conditions are studied by modifying the wedge corner and allowing for a finite radius of curvature. It is found that the type of shock reflection observed far from the corner, namely regular or Mach reflection, depends intimately on the start-up condition, as the flow "remembers" how it was started. Substantial differences were found. For example, the type of shock reflection for an incident shock Mach number M = 6.6 and an isentropic exponent γ = 1.2 changes from regular to Mach reflection between 44 • and 45 • when a straight wedge tip is used, while the transition for an initially curved wedge occurs between 57 • and 58 • .

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Classification of shock wave reflections from a wedge. Part 1: Boundaries and domains of existence for different types of reflections

Cited by 9 publications

References 9 publications

Viscous jetting and Mach stem bifurcation in shock reflections: experiments and simulations

Viscous jetting and Mach stem bifurcation in shock reflections: experiments and simulations

Formation of triple shock configurations with negative reflection angle in steady flows

Non-uniqueness of solutions in asymptotically self-similar shock reflections

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