Numerical analysis of shock wave reflection transition in steady flows

AIAA Journal ◽  
1998 ◽  
Vol 36 ◽  
pp. 2079-2086 ◽  
Author(s):  
M. S. Ivanov ◽  
G. N. Markelov ◽  
A. N. Kudryavtsev ◽  
S. F. Gimelshein
Keyword(s):  
Shock Wave ◽  
Numerical Analysis ◽  
Wave Reflection ◽  
Steady Flows ◽  
Shock Wave Reflection ◽  
Reflection Transition

Numerical Analysis of Shock Wave Reflection Transition in Steady Flows

AIAA Journal ◽  
10.2514/2.309 ◽  
1998 ◽  
Vol 36 (11) ◽  
pp. 2079-2086 ◽  
Author(s):  
M. S. Ivanov ◽  
G. N. Markelov ◽  
A. N. Kudryavtsev ◽  
S. F. Gimelshein
Keyword(s):  
Shock Wave ◽  
Numerical Analysis ◽  
Wave Reflection ◽  
Steady Flows ◽  
Shock Wave Reflection ◽  
Reflection Transition

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.

Experiments on shock wave reflection transition and hysteresis in low-noise wind tunnel

2003 ◽  
Vol 15 (6) ◽  
pp. 1807 ◽  
Author(s):  
M. S. Ivanov ◽  
A. N. Kudryavtsev ◽  
S. B. Nikiforov ◽  
D. V. Khotyanovsky ◽  
A. A. Pavlov
Keyword(s):  
Shock Wave ◽  
Wind Tunnel ◽  
Wave Reflection ◽  
Low Noise ◽  
Shock Wave Reflection ◽  
Reflection Transition

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.

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.

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