Stability of regular and Mach reflection wave configurations in steady flows

AIAA Journal ◽  
1996 ◽  
Vol 34 (10) ◽  
pp. 2196-2198 ◽  
Author(s):  
A. Chpoun ◽  
D. Passerel ◽  
G. Ben-Dor
Keyword(s):  
Mach Reflection ◽  
Steady Flows

Viscosity Effects on Mach Reflection in Steady Flows

2008 ◽  
Author(s):  
Yevgeniy Bondar ◽  
Dmitry Khotyanovsky ◽  
Alexey Kudryavtsev ◽  
Georgy Shoev ◽  
Mikhail Ivanov
Keyword(s):  
Mach Reflection ◽  
Steady Flows ◽  
Viscosity Effects

An analytical study of Mach reflection in nonequilibrium steady flows

1999 ◽  
Vol 11 (10) ◽  
pp. 3150-3167 ◽  
Author(s):  
F. Grasso ◽  
R. Paoli
Keyword(s):  
Analytical Study ◽  
Mach Reflection ◽  
Steady Flows

Analytical and experimental investigations of the reflection of asymmetric shock waves in steady flows

1999 ◽  
Vol 390 ◽  
pp. 25-43 ◽  
Author(s):  
H. LI ◽  
A. CHPOUN ◽  
G. BEN-DOR
Keyword(s):  
Shock Waves ◽  
Wave Reflection ◽  
Mach Reflection ◽  
Three Dimensional ◽  
Experimental Investigations ◽  
Hysteresis Phenomenon ◽  
Steady Flows ◽  
Shock Wave Reflection ◽  
Asymmetric Shock ◽  
The One

The reflection of asymmetric shock waves in steady flows is studied both theoretically and experimentally. While the analytical model was two-dimensional, three-dimensional edge effects influenced the experiments. In addition to regular and Mach reflection wave configurations, an inverse-Mach reflection wave configuration, which has been observed so far only in unsteady flows (e.g. shock wave reflection over concave surfaces or over double wedges) has been recorded. A hysteresis phenomenon similar to the one that exists in the reflection of symmetric shock waves has been found to also exist in the reflection of asymmetric shock waves. The domains and transition boundaries of the various types of overall reflection wave configurations are analytically predicted.

Downstream flow condition effects on the RR → MR transition of asymmetric shock waves in steady flows

2009 ◽  
Vol 620 ◽  
pp. 43-62 ◽  
Author(s):  
Z. M. HU ◽  
R. S. MYONG ◽  
M. S. KIM ◽  
T. H. CHO
Keyword(s):  
Shock Waves ◽  
Mach Reflection ◽  
Flow Structures ◽  
Steady Flows ◽  
Regular Reflection ◽  
Double Wedge ◽  
Asymmetric Reflection ◽  
Asymmetric Shock ◽  
Downstream Flow ◽  
Good Agreement

In this paper, the regular reflection (RR) to Mach reflection (MR) transition of asymmetric shock waves is theoretically studied by employing the classical two- and three-shock theories. Computations are conducted to evaluate the effects of expansion fans, which are inherent flow structures in asymmetric reflection of shock waves, on the RR → MR transition. Comparison shows good agreement among the theoretical, numerical and experimental results. Some discrepancies between experiment and theory reported in previous studies are also explained based on the present theoretical analysis. The advanced RR → MR transition triggered by a transverse wave is also discussed for the interaction of a hypersonic flow and a double-wedge-like geometry.

A parametric study of Mach reflection in steady flows

1997 ◽  
Vol 341 ◽  
pp. 101-125 ◽  
Author(s):  
H. LI ◽  
G. BEN-DOR
Keyword(s):  
Present Model ◽  
Mach Reflection ◽  
Incident Shock ◽  
Incident Shock Wave ◽  
Incoming Flow ◽  
Steady Flows ◽  
Mach Stem ◽  
Stem Height ◽  
Von Neumann ◽  
Set Up

The flow fields associated with Mach reflection wave configurations in steady flows are analysed, and an analytical model for predicting the wave configurations is proposed. It is found that provided the flow field is free of far-field downstream influences, the Mach stem heights are solely determined by the set-up geometry for given incoming-flow Mach numbers. It is shown that the point at which the Mach stem height equals zero is exactly at the von Neumann transition. For some parameters, the flow becomes choked before the Mach stem height approaches zero. It is suggested that the existence of a Mach reflection not only depends on the strength and the orientation of the incident shock wave, as prevails in von Neumann's three-shock theory, but also on the set-up geometry to which the Mach reflection wave configuration is attached. The parameter domain, beyond which the flow gets choked and hence a Mach reflection cannot be established, is calculated. Predictions based on the present model are found to agree well both with experimental and numerical results.

Influence of surface roughness on the transition from regular to Mach reflection in pseudo-steady flows

1987 ◽  
Vol 176 (-1) ◽  
pp. 333 ◽  
Author(s):  
G. Ben-Dor ◽  
G. Mazor ◽  
K. Takayama ◽  
O. Igra
Keyword(s):  
Surface Roughness ◽  
Mach Reflection ◽  
Steady Flows

The influence of the downstream pressure on the shock wave reflection phenomenon in steady flows

1999 ◽  
Vol 386 ◽  
pp. 213-232 ◽  
Author(s):  
G. BEN-DOR ◽  
T. ELPERIN ◽  
H. LI ◽  
E. VASILIEV
Keyword(s):  
Shock Wave ◽  
Wave Reflection ◽  
Numerical Study ◽  
Mach Reflection ◽  
Incident Shock ◽  
Incident Shock Wave ◽  
Steady Flows ◽  
Shock Wave Reflection ◽  
Wave Angle ◽  
Good Agreement

The effect of the downstream pressure (defined here as the wake pressure behind the tail of the reflecting wedge) on shock wave reflection in steady flows is investigated both numerically and analytically. The dependence of the shock wave configurations on the downstream pressure is studied. In addition to the incident-shock-wave-angle-induced hysteresis, which was discovered a few years ago, a new downstream- pressure-induced hysteresis has been found to exist. The numerical study reveals that when the downstream pressure is sufficiently high, an inverse-Mach reflection wave configuration, which has so far been observed only in unsteady flows, can be also established in steady flows. Very good agreement between the analytical predictions and the numerical results is found.

Further experiments on regular and Mach reflection wave configurations in steady flows

1996 ◽  
Author(s):  
A. Chpoun ◽  
D. Passerel ◽  
J. Lengrand ◽  
F. Bertrand ◽  
G. Ben-Dor
Keyword(s):  
Mach Reflection ◽  
Steady Flows
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