Downstream pressure induced hysteresis in the regular ↔ Mach reflection transition in steady flows

1997 ◽  
Vol 9 (10) ◽  
pp. 3096-3098 ◽  
Author(s):  
G. Ben-Dor ◽  
T. Elperin ◽  
H. Li ◽  
E. Vasiliev
Keyword(s):  
Mach Reflection ◽  
Steady Flows ◽  
Reflection Transition

Reconsideration of oblique shock wave reflections in steady flows. Part 1. Experimental investigation

1995 ◽  
Vol 301 ◽  
pp. 19-35 ◽  
Author(s):  
A. Chpoun ◽  
D. Passerel ◽  
H. Li ◽  
G. Ben-Dor
Keyword(s):  
Shock Wave ◽  
State Of The Art ◽  
Mach Reflection ◽  
Oblique Shock Wave ◽  
Steady Flows ◽  
Regular Reflection ◽  
Wave Reflections ◽  
Supersonic Wind Tunnel ◽  
Reflection Transition ◽  
Reflecting Surfaces

The reflection of shock waves over straight reflecting surfaces in steady flows was investigated experimentally using the supersonic wind tunnel of Laboratoire d'Aerothermique du CNRS, Meudon, France. The results for a flow Mach number M0 = 4.96 contradict the state of the art regarding the regular [harr ] Mach reflection transition in steady flows. Not only was a hysteresis found to exist in this transition, but, unlike previous reports, regular reflection configurations were found to be stable in the dual-solution domain in which theoretically both regular and Mach reflection are possible.

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.

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