Transition from regular reflection to mach reflection when a shock wave interacts with a wall in a two-phase gas?liquid medium

1984 ◽  
Vol 18 (5) ◽  
pp. 827-829 ◽  
Author(s):  
A. V. Voloshinov ◽  
A. D. Kovalev ◽  
G. P. Shindyapin
Keyword(s):  
Shock Wave ◽  
Liquid Medium ◽  
Mach Reflection ◽  
Regular Reflection ◽  
Two Phase

Experimental investigation of the propagation of a planar shock wave through a two-phase gas-liquid medium

2011 ◽  
Vol 23 (11) ◽  
pp. 113301 ◽  
Author(s):  
A. Chauvin ◽  
G. Jourdan ◽  
E. Daniel ◽  
L. Houas ◽  
R. Tosello
Keyword(s):  
Shock Wave ◽  
Experimental Investigation ◽  
Liquid Medium ◽  
Two Phase ◽  
Planar Shock ◽  
Planar Shock Wave

scholarly journals Отрицательное маховское отражение с множественными тройными конфигурациями при дифракции ударной волны на клине

2021 ◽  
Vol 47 (20) ◽  
pp. 11
Author(s):  
П.Ю. Георгиевский ◽  
А.Н. Максимов ◽  
В.П. Фокеев
Keyword(s):  
Shock Wave ◽  
Euler Equations ◽  
Numerical Study ◽  
Mach Reflection ◽  
Wedge Angle ◽  
Regular Reflection ◽  
Self Similar

Within the framework of the Euler equations, a numerical study of the structure of a self-similar flow for various types of negative Mach reflection during diffraction of a shock wave by a wedge is performed. Along with the known modes of double and triple Mach reflection, a qualitatively new mode of negative Mach reflection with multiple three-shock configurations is observed. Peculiarities of the transition from multiple Mach reflection to regular reflection when changing the wedge angle are noted.

Theory of regular and mach reflection of shock waves in a two-phase gas-liquid medium

1985 ◽  
Vol 20 (2) ◽  
pp. 332-334
Author(s):  
A. V. Voloshinov ◽  
A. D. Kovalev ◽  
G. P. Shindyapin
Keyword(s):  
Shock Waves ◽  
Liquid Medium ◽  
Mach Reflection ◽  
Two Phase

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.

The non-stationary hysteresis phenomenon in shock wave reflections

2013 ◽  
Vol 732 ◽  
Author(s):  
Meital Geva ◽  
Omri Ram ◽  
Oren Sadot
Keyword(s):  
Shock Wave ◽  
High Resolution ◽  
Triple Point ◽  
Convex Surface ◽  
Mach Reflection ◽  
Incident Shock ◽  
Incident Shock Wave ◽  
Concave Surface ◽  
Hysteresis Phenomenon ◽  
Regular Reflection

AbstractThe non-stationary transition from Mach to regular reflection followed by a reverse transition from regular to Mach reflection is investigated experimentally. A new experimental setup in which an incident shock wave reflects from a cylindrical concave surface followed by a cylindrical convex surface of the same radius is introduced. Unlike other studies that indicate problems in identifying the triple point, an in-house image processing program, which enables automatic detection of the triple point, is developed and presented. The experiments are performed in air having a specific heats ratio 1.4 at three different incident-shock-wave Mach numbers: 1.2, 1.3 and 1.4. The data are extracted from high-resolution schlieren images obtained by means of a fully automatically operated shock-tube system. Each experiment produces a single image. However, the high accuracy and repeatability of the control system together with the fast opening valve enables us to monitor the dynamic evolution of the shock reflections. Consequently, high-resolution results both in space and time are obtained. The credibility of the present analysis is demonstrated by comparing the first transition from Mach to regular reflection ($\mathrm{MR} \rightarrow \mathrm{RR} $) with previous single cylindrical concave surface experiments. It is found that the second transition, back to Mach reflection ($\mathrm{RR} \rightarrow \mathrm{MR} $), occurs earlier than one would expect when the shock reflects from a single cylindrical convex surface. Furthermore, the hysteresis is observed at incident-shock-wave Mach numbers smaller than those at which the dual-solution domain starts, which is the minimal value for obtaining hysteresis in steady and pseudo-steady flows. The existence of a non-stationary hysteresis phenomenon, which is different from the steady-state hysteresis phenomenon, is discovered.

The regular reflection→Mach reflection transition in unsteady flow over convex surfaces

2017 ◽  
Vol 837 ◽  
pp. 48-79 ◽  
Author(s):  
M. Geva ◽  
O. Ram ◽  
O. Sadot
Keyword(s):  
Shock Wave ◽  
Mach Reflection ◽  
Incident Shock ◽  
Stem Growth ◽  
Mach Stem ◽  
Regular Reflection ◽  
Flow Properties ◽  
Numerical Computations ◽  
Convex Surfaces ◽  
Reflecting Surface

The non-stationary transition from regular reflection (RR) to Mach reflection (MR) over convex segments has been the focus of many recent studies. Until recently, the problem was thought to be very complicated because it was believed that many parameters such as the radius of curvature, initial angle and geometrical shape of the reflecting surface influenced this process. In this study, experiments and inviscid numerical computations were performed in air ($\unicode[STIX]{x1D6FE}=1.4$) at an incident shock-wave Mach number of 1.3. The incident shock waves were reflected over cylindrical and elliptical convex surfaces. The computations were validated by high-resolution experiments, which enabled the detection of features in the flow having characteristic lengths as small as 0.06 mm. Therefore, the RR →MR transition and Mach stem growth were successfully validated in the early stages of the Mach stem formation and closer to the surface than ever before. The evolution of the RR, the transition to MR and the Mach stem growth were found to depend only on the radius of the reflecting surface. The reflected shock wave adjusts itself to the changing angles of the reflecting surface. This feature, which was demonstrated at Mach numbers 1.3 and 1.5, distinguishes the unsteady case from the self-similar pseudo-steady case and requires the formulation of the conservation equations. A modification of the standard two-shock theory (2ST) is presented to predict the flow properties behind a shock wave that propagates over convex surfaces. Until recently, the determination of the time-dependent flow properties was possible solely by numerical computations. Moreover, this derivation explains the controversial issue on the delay in the transition from the RR to the MR that was observed by many researchers. It turns out that the entire RR evolution and the particular moment of transition to MR, are based on the essential ‘no-penetration’ condition of the flow. Therefore, we proposed a simple geometrical criterion for the RR →MR transition.

The Numerical Modeling of Spherical Explosion in the Foam

2016 ◽  
Vol 11 (1) ◽  
pp. 60-65 ◽  
Author(s):  
R.Kh. Bolotnova ◽  
E.F. Gainullina
Keyword(s):  
Shock Wave ◽  
Numerical Modeling ◽  
Initial Pressure ◽  
Water Volume ◽  
Symmetric Model ◽  
Two Phase ◽  
Experimental Conditions ◽  
Initial Water ◽  
Aqueous Foam ◽  
Spherical Explosion

The spherical explosion propagation process in aqueous foam with the initial water volume content α10=0.0083 corresponding to the experimental conditions is analyzed numerically. The solution method is based on the one-dimensional two-temperature spherically symmetric model for two-phase gas-liquid mixture. The numerical simulation is built by the shock capturing method and movable Lagrangian grids. The amplitude and the width of the initial pressure pulse are found from the amount of experimental explosive energy. The numerical modeling results are compared to the real experiment. It’s shown, that the foam compression in the shock wave leads to the significant decrease in velocity and in amplitude of the shock wave.

Features of spatial shock-wave flows in vapor-gas-liquid mixtures

2014 ◽  
Vol 10 ◽  
pp. 27-31
Author(s):  
R.Kh. Bolotnova ◽  
U.O. Agisheva ◽  
V.A. Buzina
Keyword(s):  
Shock Wave ◽  
High Pressure ◽  
Shock Waves ◽  
Liquid Mixture ◽  
Liquid Mixtures ◽  
Pressure Vessels ◽  
Water Mixture ◽  
Two Dimensional ◽  
Nonstationary Processes ◽  
Two Phase

The two-phase model of vapor-gas-liquid medium in axisymmetric two-dimensional formulation, taking into account vaporization is constructed. The nonstationary processes of boiling vapor-water mixture outflow from high-pressure vessels as a result of depressurization are studied. The problems of shock waves action on filled by gas-liquid mixture volumes are solved.

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.

Sign in / Sign up

Export Citation Format

Share Document