16: Interaction of an Expansion Wave with a Shock Wave and a Shock Wave Curvature

2015 ◽  
pp. 279-294
Keyword(s):  
Shock Wave ◽  
Expansion Wave ◽  
Wave Curvature

On the flow near a weak shock wave downstream of a nozzle throat

1975 ◽  
Vol 69 (1) ◽  
pp. 97-108 ◽  
Author(s):  
A. F. Messiter ◽  
T. C. Adamson
Keyword(s):  
Shock Wave ◽  
Fluid Motion ◽  
Axisymmetric Flow ◽  
Weak Shock ◽  
Small Region ◽  
Jump Conditions ◽  
Nozzle Throat ◽  
Streamline Curvature ◽  
Two Dimensional Flow ◽  
Wave Curvature

In a transonic nozzle flow in which the velocity is slightly supersonic in some neighbourhood of the nozzle throat, a shock wave may be present either very close to the throat or else somewhat further downstream. In the latter case, relatively simple series solutions in general provide an asymptotic description of the fluid motion except very close to the shock wave. These outer solutions are reviewed for symmetric two-dimensional flow, and it is shown that the shock-wave jump conditions are not satisfied. A correction is then derived in the form of an inner solution for a small region immediately behind the shock. The resulting solution exhibits the singularities in the pressure gradient, streamline curvature and shock-wave curvature which are expected to occur at the intersection of a normal shock wave and a curved wall. An extension to axisymmetric flow is also given.

Shock-wave/expansion-wave interactions and the transition between regular and Mach reflection

2007 ◽  
Vol 575 ◽  
pp. 399-424 ◽  
Author(s):  
R. HILLIER
Keyword(s):  
Shock Wave ◽  
Numerical Simulations ◽  
Solid Surface ◽  
Narrow Range ◽  
Mach Reflection ◽  
Incident Shock ◽  
Incident Shock Wave ◽  
Expansion Wave ◽  
Incident Flow ◽  
Wave Interactions

This paper presents numerical simulations for the interaction of an expansion wave with an incident shock wave of the opposite family, the specific aim being to study the resultant reflection of the now-perturbed shock wave from a solid surface. This problem is considered in the context of an incident flow entering a parallel duct, a situation that commonly arises in a range of flow-turning problems including supersonic intake flows. Once the incident shock conditions are such that Mach reflection must occur, it is shown that stabilization of a simple Mach reflection is only possible for a narrow range of Mach numbers and that this depends sensitively on the relative streamwise positioning of the origins of the shock wave and the expansion wave.

Boundary layers in superfluid flows and their influence on shock wave curvature

1995 ◽  
Vol 212 (2) ◽  
pp. 144-148
Author(s):  
G Stamm ◽  
J Piechna ◽  
W Fiszdon
Keyword(s):  
Shock Wave ◽  
Boundary Layers ◽  
Wave Curvature

Internal flow mechanism in a supersonic expander-rotor

2021 ◽  
pp. 095441002110236
Author(s):  
Zhenyu Huang ◽  
Jingjun Zhong
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Flow Structure ◽  
Internal Flow ◽  
Leading Edge ◽  
Wave Structure ◽  
Oblique Shock ◽  
Expansion Wave ◽  
Oblique Shock Wave ◽  
Flow Mechanism

This article proposes a numerical investigation into the internal flow structure in the supersonic expander-rotor (SER). In order to reveal internal flow mechanism, the significant influencing factors in the flow structure are identified, and the solutions to improving the integrated performance of the SER are developed. According to the numerical results, the wave structure of the expansion wave and the oblique shock wave is what characterizes the flow in the mainstream region of the SER. In addition, the expansion wave and the oblique shock wave impose control on the pattern of static pressure distribution in the 3-D channel and then the 3-D flow structure. The formation and breakdown of the tip leakage vortex are the main form that the motion of vortex takes in the SER. The concentration, recirculation, and separation of the boundary layer; the low energy fluid mixing with mainstream; and the interaction between the oblique shock waves and the boundary layer are the crucial motion tracing near the endwall. Compared with the traditional turbines, the flow structures in the tip region of the SER are relatively simpler; the essential motion tracing is the airflow near the leading edge of the strake wall moving from the PS through the tip gap to the SS as a result of the transverse pressure difference.

On the irregular refraction of a plane shock wave at a Mach number interface

1968 ◽  
Vol 32 (1) ◽  
pp. 185-202 ◽  
Author(s):  
L. F. Henderson ◽  
A. K. Macpherson
Keyword(s):  
Shock Wave ◽  
Mach Number ◽  
Speed Of Sound ◽  
Expansion Wave ◽  
Plane Shock Wave ◽  
Plane Shock ◽  
Irregular Wave ◽  
Self Similar ◽  
Irregular Systems ◽  
Mach Reflexion

The paper considers the refraction of a plane shock wave at an interface between two streams of different Mach number. Particular attention is paid to the irregular wave systems. It is found that when the interface is slow-fast, that is when the speed of sound a0 in the first or incident wave medium is less than the speed of sound aB in the second or transmitted wave medium, then there are two irregular systems, one being a double Mach reflexion type and the other being a four-wave confluence type. There are also two irregular systems when the refraction is fast-slow; these are a single Mach reflexion type and an expansion wave type. This last system has a central expansion wave when the flow is steady and a continuous band expansion wave when the flow is self-similar. Only two of the irregular wave systems have been observed experimentally in the fully developed state. Possible degeneracies are discussed.

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