Starting Jet–wall Interaction

Szumowski, A. P.; Sobieraj, G.; Selerowicz, W. C.; Piechna, Janusz

doi:10.1006/jsvi.1999.2772

Cited by 9 publications

(3 citation statements)

References 4 publications

(1 reference statement)

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“…Kontis et al [15] conducted a similar experimental study to examine the interaction of shock wave induced vortices with a flat plate and a perforated plate. Apart from the consistent observations with those obtained by Szumowski et al [14], they observed and analyzed the production of a wall vortex (or secondary vortex ring) for the flat plate case, furthermore, the transmission and reflection of the shock wave respectively flowed by compression waves, and the dissipation of the jet accompanied by the vortices inside and outside the pores for the perforated plate case. Igra et al [16] used a two-dimensional, compressible, inviscid flow model to numerically study the influence of a series of flat barriers on shock wave attenuation in the channel.…”

Section: Introductionsupporting

confidence: 73%

“…The experimental results demonstrated that the velocity and stability of the reflected shock wave increased with the increase in the density and length of the foam barrier. Szumowski et al [14] experimentally and numerically investigated the interaction of a reflected shock wave and a ring vortex occurring in the impingement of a jet starting from a shock tube on a perpendicular solid wall. The main findings included: (1) a toroidal sound wave generates, meanwhile, the shock wave deforms during the interaction; and (2) the impingement of the ring vortex on the wall also causes the generation of sound waves.…”

Section: Introductionmentioning

confidence: 99%

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Numerical Study of Air Flow Induced by Shock Impact on an Array of Perforated Plates

Zhang

Feng

Sun

et al. 2021

Entropy

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This study is focused on the propagation behavior and attenuation characteristics of a planar incident shock wave when propagating through an array of perforated plates. Based on a density-based coupled explicit algorithm, combined with a third-order MUSCL scheme and the Roe averaged flux difference splitting method, the Navier–Stokes equations and the realizable k-ε turbulence model equations describing the air flow are numerically solved. The evolution of the dynamic wave and ring vortex systems is effectively captured and analyzed. The influence of incident shock Mach number, perforated-plate porosity, and plate number on the propagation and attenuation of the shock wave was studied by using pressure- and entropy-based attenuation rates. The results indicate that the reflection, diffraction, transmission, and interference behaviors of the leading shock wave and the superimposed effects due to the trailing secondary shock wave are the main reasons that cause the intensity of the leading shock wave to experience a complex process consisting of attenuation, local enhancement, attenuation, enhancement, and attenuation. The reflected shock interactions with transmitted shock induced ring vortices and jets lead to the deformation and local intensification of the shock wave. The formation of nearly steady jets following the array of perforated plates is attributed to the generation of an oscillation chamber for the inside dynamic wave system between two perforated plates. The vorticity diffusion, merging and splitting of vortex cores dissipate the wave energy. Furthermore, the leading transmitted shock wave attenuates more significantly whereas the reflected shock wave from the first plate of the array attenuates less significantly as the shock Mach number increases. The increase in the porosity weakens the suppression effects on the leading shock wave while increases the attenuation rate of the reflected shock wave. The first perforated plate in the array plays a major role in the attenuation of the shock wave.

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Section: Introductionsupporting

confidence: 73%

Section: Introductionmentioning

confidence: 99%

Numerical Study of Air Flow Induced by Shock Impact on an Array of Perforated Plates

Zhang

Feng

Sun

et al. 2021

Entropy

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“…They identified the mechanism of shocklet formation near the wall. Szumowski et al [4] studied the starting jet interaction with the wall kept at x/D = 2 using Schlieren technique for jet Mach number varying from 0.65 to 1.14 and found toroidal waves generated during shock-vortex ring interaction. They also measured wall pressure along the radial plane.…”

Section: Introductionmentioning

confidence: 99%

Characteristics of Noise Produced during Impingement of a Compressible Vortex Ring on a Wall

Thangadurai

Das

2010

International Journal of Aeroacoustics

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Noise produced during normal impingement of a compressible vortex ring on a flat surface is studied in the shock-Mach number (M) range of 1.31 to 1.55. The compressible vortex ring is generated at the open end of a short driver section shock tube. The far-field noise is decomposed into three major components; (i) sound field due to formation and evolution of the vortex ring, (ii) reflected shock and vortex ring interaction noise and (iii) noise due to impingement of the ring on the wall. The impingement noise consists of fluctuating pressure due to deformation and stretching of the vortex ring, formation and growth of a secondary wall vortex ring, lifting-off of the primary-secondary vortex ring pair. All these events are identified using discrete wavelet transform (DWT) of the sound pressure signal and verified with the laser sheet based flow visualizations. Acoustics fluctuations measured at different angular location shows that the noise due to wall-vortex ring interaction is dominant at 10°≤ θ ≤ 40°.

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