An Interferometric Investigation of the Regular to Mach Reflection Transition Boundary in Pseudostationary Flow in Air.

1986 ◽  
Author(s):  
John Wheeler
Keyword(s):  
Mach Reflection ◽  
Transition Boundary ◽  
Reflection Transition ◽  
Interferometric Investigation

scholarly journals Hysteresis processes in the regular reflection↔Mach reflection transition in steady flows

2002 ◽  
Vol 38 (4-5) ◽  
pp. 347-387 ◽  
Author(s):  
G Ben-Dor ◽  
M Ivanov ◽  
E.I Vasilev ◽  
T Elperin
Keyword(s):  
Mach Reflection ◽  
Steady Flows ◽  
Regular Reflection ◽  
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.

Three-dimensional shock wave reflection transition in steady flow

2018 ◽  
Vol 858 ◽  
pp. 565-587 ◽  
Author(s):  
Divek Surujhlal ◽  
Beric W. Skews
Keyword(s):  
Shock Wave ◽  
Wave Reflection ◽  
Numerical Models ◽  
Dimensional Space ◽  
Mach Reflection ◽  
Three Dimensional ◽  
Flow Fields ◽  
Shock Wave Reflection ◽  
Sweep Angle ◽  
Reflection Transition

Three-dimensional shock wave reflection comprises flow physics that is significantly different from the well-documented two-dimensional cases in a number of aspects. The most important differentiating factor is the sweep of the shock system. In particular, this work examines the nature of flow fields in which there is a transition of shock reflection configuration in three-dimensional space. The flow fields investigated have been made to exist in the absence of edge effects influencing the shock interaction and transition, as found previously to exist in conventional double-wedge studies. In general, the shock configurations are those with central regular and peripheral Mach reflection portions. It is shown that the sweep angle of the portions on either side of the transition point is subject to a cusp, as per an analytical model that is developed. This is confirmed with the use of numerical models with additional evidence provided by experimental results using oblique shadow photography. Further application of the principles of three-dimensional shock analysis and those pertaining to the sweep cusp model yield important insights regarding the overall shock geometry and that at transition.

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

Regular to Mach reflection transition in truly nonstationary flows - Influence of surface roughness

AIAA Journal ◽  
1981 ◽  
Vol 19 (9) ◽  
pp. 1238-1240 ◽  
Author(s):  
K. Takayama ◽  
G. Ben-Dor ◽  
J. Gotoh
Keyword(s):  
Surface Roughness ◽  
Mach Reflection ◽  
Reflection Transition

Experimental confirmation of the von Neumann theory of shock wave reflection transition

2002 ◽  
Vol 472 ◽  
pp. 263-282 ◽  
Author(s):  
FILIPE J. BARBOSA ◽  
BERIC W. SKEWS
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Wave Reflection ◽  
Solid Wall ◽  
Mach Reflection ◽  
Reflected Shock Wave ◽  
Shock Wave Reflection ◽  
Trailing Edge ◽  
Reflected Shock ◽  
Reflection Transition

For many years there has been debate regarding why shock wave reflection off a solid surface has allowed regular reflection to persist beyond the incidence angles where it becomes theoretically impossible. Theory predicts that at some limiting angle the reflection point will move away from the wall and Mach reflection will occur. Previous studies have suggested that the paradox could be due to the presence of the growing viscous boundary layer immediately behind the point of reflection, and some numerical studies support this view. This paper takes the approach of establishing an experimental facility in which the theoretical assumptions regarding the surface of reflection are met, i.e. that the reflecting surface is perfectly smooth, perfectly rigid, and adiabatic. This is done by constructing a bifurcated shock tube facility in which a shock wave is split into two plane waves that are then allowed to reflect off each other at the trailing edge of wedge. The plane of symmetry between the waves then acts as the perfect reflection surface.Through a careful set of visualization experiments, and the use of multivariate analysis to take account of the uncertainty in shock Mach number, triple-point trajectory angle, and slightly different shock wave arrival times at the trailing edge, the current work shows that the transition from one type of reflection to the other does indeed occur at the theoretical value. Conventional tests of reflection off a solid wall show significantly different transition results. Furthermore, it is also shown that the thermal boundary layer plays an important role in this regard. It is thus confirmed that viscous and thermal effects are the reason for the paradox. Reasons are also suggested for the counter-intuitive behaviour of the reflected shock wave angle.

Time history of regular to Mach reflection transition in steady supersonic flow

2011 ◽  
Vol 682 ◽  
pp. 160-184 ◽  
Author(s):  
S. G. LI ◽  
B. GAO ◽  
Z. N. WU
Keyword(s):  
Triple Point ◽  
Early Stage ◽  
Mach Reflection ◽  
Time History ◽  
Mach Stem ◽  
Interaction Structure ◽  
Reflection Transition ◽  
History Of ◽  
Multiple Interaction ◽  
Mach Waves

In this paper, we study the transition from regular to Mach reflection (RR → MR) in the dual solution domain due to the influence of an upstream disturbance, by considering the transition as an evolutionary rather than an abrupt process. From numerical simulation, we observe for the early stage of transition a multiple interaction structure, composed of a triple-shock structure, a type VI shock interaction and a shock/slipline interaction. In the end, we observe a pure unsteady MR structure. Under self-similar assumption of the triple point for the first stage and including additional Mach waves over the slipline for the last stage, we develop an idealized unsteady model to obtain the evolution of the Mach stem height and the time taken for the Mach stem to stabilize. The triple point is found to move at a nearly constant speed in the multiple interaction stage which occupies about one quarter of the transition time. In the pure unsteady MR stage, which occupies the rest of transition, the speed of the triple point drops nonlinearly until the Mach stem stabilizes.

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