Shock-free compressible vortex rings impinging on a stationary surface: Effects of surface angle variation

Mariani, Raffaello; Quinn, Mark K.; Kontis, Konstantinos; Marraffa, L.

doi:10.1016/j.expthermflusci.2013.01.008

Cited by 10 publications

(3 citation statements)

References 32 publications

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“…Such scenarios will be of special interest, as they entail the direct impact and subsequent interactions between two vortex rings or a vortex ring and solid/non-solid boundaries, as opposed to a discrete vortex-ring entity assumed to be free (or largely free) of external influences. Such scenarios have been studied systematically earlier, including but not limited to those reported by Walker et al (1987), Lim (1989), Lim, Nickels & Chong (1991), Orlandi & Verzicco (1993), Verzicco & Orlandi (1994), Chu, Wang & Chang (1995), Swearingen, Crouch & Handler (1995), Fabris, Liepmann & Marcus (1996), Minota, Nishida & Lee (1997), Naitoh, Banno & Yamada (2001), Arévalo et al (2007), Cheng, Lou & Luo (2010), Couch & Krueger (2011), Mariani et al (2013), New, Shi & Zang (2016) and Xu & Wang (2016) for flat/inclined-walls, Adhikari & Lim (2009), Hrynuk, Van Luipen & Bohl (2012), Naaktgeboren, Krueger & Lage (2012), Cheng, Lou & Lim (2014) and Xu et al (2018) for porous walls, Orlandi (1993), Naitoh, Sun & Yamada (1995), Ren, Zhang & Guan (2015) and New & Zang (2017) for round cylinders, and, more recently, a scenario whereby a vortex ring collides upon a wall with a circular aperture investigated by Hu & Peterson (2018).…”

Section: Introductionmentioning

confidence: 99%

Collision of vortex rings upon V-walls

et al. 2020

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Section: Introductionmentioning

confidence: 99%

Collision of vortex rings upon V-walls

et al. 2020

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“…The shock wave produces a high pressure and a high temperature as well as induced high speed flow. Since the magnitude of these flow features depends on the initial pressure ratio between the driver and driven sections as well as the specific heat ratio of gas medium, shock tubes can be used to study aerodynamic flows in a wide range of temperatures and pressures, which are difficult to obtain in other types of testing facilities [4][5][6][7][8][9][10][11][12][13][14][15][16]. Additionally, shock tubes are applicable to fundamental research in medicine, biology, and industries [17][18][19][20][21][22][23].…”

Section: Introductionmentioning

confidence: 99%

Characterization of a novel open-ended shock tube facility based on detonation transmission tubing

Ukai

Kontis

2019

Aerospace Science and Technology

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This paper proposes and demonstrates a novel shock tube driven by commercially available detonation transmission tubing in a safe, repeatable, and controllable manner for laboratory scale experiments. A circular cross-sectional open-ended shock tube (inner-diameter D = 22 mm) driven by detonation transmission tubing was used to investigate the working principle of this novel shock tube using a dynamic pressure transducer and time-resolved shadowgraph photography. Specifically, the shock Mach number, repeatability, and flow structure generated from the tube exit were characterized. The experimental result shows that the flow structure including an initial shock wave, a vortex ring, an embedded shock, and an oblique shock pattern is similar to that of the conventional compressed-gas driven shock tubes. Furthermore, the shock tube has good repeatability of less than 2% with a shock Mach number up to 1.58. The versatile and cost-effective nature of the shock tube driven by detonation transmission tubing opens a new horizon for shock wave-assisted interdisciplinary applications.

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“…Shock waves generated in supersonic jets are often accompanied by induced vortex rings [17][18][19], and there is a high possibility that these flows interact with each other, which results in noise generation.…”

Section: Introductionmentioning

confidence: 99%

Three-dimensional shock wave distortion in shock-square vortex loop interaction

Ukai

Zare‐Behtash

Kontis

et al. 2016

Experimental Thermal and Fluid Science

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Abstract:Understanding of the three-dimensional shock wave-vortex loop interaction phenomena plays a key role in noise reduction. This study focuses on the three-dimensional shock wave distortion and propagation phenomena in a near-field supersonic jet. Shock-square vortex loop interaction was experimentally investigated in a square cross-sectional open-end shock wave generating tube at an incident shock Mach number of 1.39 ± 0.05. A square vortex loop impinged on a reflected shock wave from a wall located in front of the nozzle end. The planar reflected shock wave transforms into either a concave or convex distorted shape due to the opposing high-speed flow emitted from the nozzle corner. The convex shaped shock wave scatters towards the outside of the vortex loop, whereas the concave one converges towards the centre of the vortex loop. The concave shaped shock wave results in shock wave focusing. In shock-square vortex loop interaction, the shock wave is locally focused along the axis of the nozzle corner. Keywords:Shock wave interaction; square vortex loop; shock wave focusing 2

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Shock-free compressible vortex rings impinging on a stationary surface: Effects of surface angle variation

Cited by 10 publications

References 32 publications

Collision of vortex rings upon V-walls

Collision of vortex rings upon V-walls

Characterization of a novel open-ended shock tube facility based on detonation transmission tubing

Three-dimensional shock wave distortion in shock-square vortex loop interaction

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