Numerical investigations of transition between regular and Mach reflections caused by free-stream disturbances

Kudryavtsev, A. N.; Khotyanovsky, D. V.; Иванов, М. С.; Hadjadj, A.; Vandromme, D.

doi:10.1007/s00193-002-0150-5

Cited by 38 publications

(38 citation statements)

References 17 publications

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“…This plane is divided by two curves (the von Neumann criterion θ = θ N (M 0 ) and the detachment criterion θ = θ D (M 0 )) into three branches: lower branch for only RR, upper branch for only MR and middle branch where both RR and MR are possible depending on the history that the actual steady flow is built (see Ben-Dor 2007 and references therein). Although both RR and MR are stable with small disturbances in the dual solution domain (Teshukov 1989;Li & Ben-Dor 1996), RR may transit to MR if the amplitude of the disturbance exceeds a certain level (Ivanov et al 1997(Ivanov et al , 1998(Ivanov et al , 2000Kudryavtsev et al 2002). The earlier investigations (e.g.…”

Section: Introductionmentioning

confidence: 94%

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

Gao

2011

J. Fluid Mech.

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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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Section: Introductionmentioning

confidence: 94%

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

Gao

2011

J. Fluid Mech.

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“…The experimental work on three-dimensionality was also accompanied by computations [8]. The effect of free-stream disturbances was investigated computationally by Kudryavtsev et al [9] and experimentally by Ivanov et al [6].…”

Section: Contributions Of Mikhail Ivanov and His Teammentioning

confidence: 99%

Mach reflection in steady flow. I. Mikhail Ivanov's contributions, II. Caltech stability experiments

Hornung¹

2014

AIP Conference Proceedings

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Abstract. To honor the memory of our friend and colleague Mikhail Ivanov a review of his great contributions to the understanding of the various phenomena associated with steady-flow shock wave reflection is presented. Of course, he has contributed much more widely than that, but I will restrict myself to this part of his work, because it is what I understand best. In particular, his computational and experimental demonstration of hysteresis in the transition between regular and Mach reflection, and his resolution of the difficulties associated with the triple point in weak Mach reflection in terms of the effects of viscosity and heat conduction are reviewed. Finally, some experimental results are presented that demonstrate that, in the dual-solution domain, Mach reflection is more stable than regular reflection.

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“…The difference between the angles of forward and back transitions measured in wind-tunnel experiments, however, can depend on the level of flow disturbances inherent in the facility [12]. Within the dual solution domain, the flow disturbances are able to induce the transition from the regular to Mach reflection [13], so that the hysteresis can completely disappear in a noisy experimental facility. On the contrary, the largest difference is observed in a low-noise wind tunnel: the transition to the Mach reflection occurs near α d while the reverse transition happens very close to α N [14].…”

Section: Introductionmentioning

confidence: 99%

Hysteresis phenomenon at interaction of shock waves generated by a cylinder array

Kudryavtsev

Epstein

2012

Shock Waves

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This paper describes investigations of the interaction between bow shock waves generated by cylindrical bodies in a supersonic flow. Numerical simulations are performed using the inviscid Euler equations for cylinders whose axes are parallel to each other and normal to the flow direction. Mostly an infinite periodical cylinder array is considered, but the case of two cylinders is also briefly discussed. Three different regimes of the shock wave interaction, a regular interaction, a Mach interaction, and a choked flow, have been observed for the flow through the periodical cylinder array. In the case of the flow around two bodies, the choked flow is replaced by a regime with a collective bow shock. The transition between different flow regimes is studied by varying the inflow Mach number or the distance between the cylinders. A hysteretic behavior at the transition between the regular and Mach interactions has been observed. The transition is governed by the theoretical detachment and von Neumann criteria based on the local shock wave inclination at the interaction point.

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Numerical investigations of transition between regular and Mach reflections caused by free-stream disturbances

Cited by 38 publications

References 17 publications

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

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

Mach reflection in steady flow. I. Mikhail Ivanov's contributions, II. Caltech stability experiments

Hysteresis phenomenon at interaction of shock waves generated by a cylinder array

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