Numerical simulation of Mach reflection in steady flows

2001 ◽  
Author(s):  
J. Schmisseur ◽  
Datta Gaitonde
Keyword(s):  
Numerical Simulation ◽  
Mach Reflection ◽  
Steady Flows

Numerical simulation of Mach reflection in steady flows

Shock Waves ◽  
2011 ◽  
Vol 21 (6) ◽  
pp. 499-509 ◽  
Author(s):  
J. D. Schmisseur ◽  
D. V. Gaitonde
Keyword(s):  
Numerical Simulation ◽  
Mach Reflection ◽  
Steady Flows

The reflection of asymmetric shock waves in steady flows: a numerical investigation

2002 ◽  
Vol 469 ◽  
pp. 71-87 ◽  
Author(s):  
M. S. IVANOV ◽  
G. BEN-DOR ◽  
T. ELPERIN ◽  
A. N. KUDRYAVTSEV ◽  
D. V. KHOTYANOVSKY
Keyword(s):  
Numerical Simulation ◽  
Experimental Investigation ◽  
Shock Waves ◽  
Numerical Investigation ◽  
Theoretical Study ◽  
Mach Reflection ◽  
Hysteresis Phenomenon ◽  
Steady Flows ◽  
Regular Reflection ◽  
Asymmetric Shock

The theoretical study and experimental investigation of the reflection of asymmetric shock waves in steady flows reported by Li et al. (1999) are complemented by a numerical simulation. All the findings reported in both the theoretical study and the experimental investigation were also evident in the numerical simulation. In addition to weak regular reflection and Mach reflection wave configurations, strong regular reflection and inverse-Mach reflection wave configurations were recorded numerically. The hysteresis phenomenon, which was hypothesized in the course of the theoretical study and then verified in the experimental investigation, was also observed in the numerical simulation.

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

Gaseous detonation propagation in a bifurcated tube

2008 ◽  
Vol 599 ◽  
pp. 81-110 ◽  
Author(s):  
C. J. WANG ◽  
S. L. XU ◽  
C. M. GUO
Keyword(s):  
Numerical Simulation ◽  
Detonation Wave ◽  
Mach Reflection ◽  
Initial Pressure ◽  
Gaseous Detonation ◽  
Recirculation Region ◽  
Horizontal Branch ◽  
Regular Reflection ◽  
Detonation Propagation ◽  
Wall Geometry

Gaseous detonation propagation in a bifurcated tube was experimentally and numerically studied for stoichiometric hydrogen and oxygen mixtures diluted with argon. Pressure detection, smoked foil recording and schlieren visualization were used in the experiments. Numerical simulation was carried out at low initial pressure (8.00kPa), based on the reactive Navier–Stokes equations in conjunction with a detailed chemical reaction model. The results show that the detonation wave is strongly disturbed by the wall geometry of the bifurcated tube and undergoes a successive process of attenuation, failure, re-initiation and the transition from regular reflection to Mach reflection. Detonation failure is attributed to the rarefaction waves from the left-hand corner by decoupling leading shock and reaction zones. Re-initiation is induced by the inert leading shock reflection on the right-hand wall in the vertical branch. The branched wall geometry has only a local effect on the detonation propagation. In the horizontal branch, the disturbed detonation wave recovers to a self-sustaining one earlier than that in the vertical branch. A critical case was found in the experiments where the disturbed detonation wave can be recovered to be self-sustaining downstream of the horizontal branch, but fails in the vertical branch, as the initial pressure drops to 2.00kPa. Numerical simulation also shows that complex vortex structures can be observed during detonation diffraction. The reflected shock breaks the vortices into pieces and its interaction with the unreacted recirculation region induces an embedded jet. In the vertical branch, owing to the strength difference at any point and the effect of chemical reactions, the Mach stem cannot be approximated as an arc. This is different from the case in non-reactive steady flow. Generally, numerical simulation qualitatively reproduces detonation attenuation, failure, re-initiation and the transition from regular reflection to Mach reflection observed in experiments.

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.

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