About the Secondary Separation at Supersonic Flow Over a Compression Ramp

Shvedchenko, Vladimir Viktorovich

doi:10.1615/tsagiscij.v40.i5.60

Cited by 20 publications

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“…It is only in recent years that existence of secondary vortices in large separated regions induced at a compression corner have been discussed by Neiland et al. (2008) and Shvedchenko (2009), Egorov et al. (2011).…”

Section: The Compression Corner Geometrymentioning

confidence: 99%

“…In recent years, in several investigations of supersonic and hypersonic shock wave/boundary layer interactions (SBLI) involving large separated regions, numerical studies have shown multiple vortex structures/eddies embedded in the main separation bubble (Smith & Khorrami 1991; Korolev, Gajjar & Ruban 2002; Neiland, Sokolov & Shvedchenko 2008; Shvedchenko 2009). The critical parameter governing the origin and existence of these eddies seems to be the geometric angle , which represents the strength of perturbation to the boundary layer such as a shock wave inducing separation at a compression corner or a shock wave from a wedge incident on a boundary layer growing over a surface such as a flat plate beneath the wedge.…”

Section: Introductionmentioning

confidence: 99%

“…Further, dependence of such multiple eddies on wall temperature and Reynolds number has recently been investigated by Neiland et al. (2008) and Shvedchenko (2009), Egorov, Neiland & Shvedchenko (2011) and Khraibut et al. (2017) in the context of hypersonic SBLI.…”

Section: Introductionmentioning

confidence: 99%

“…For example, Neiland et al. (2008) and Shvedchenko (2009) have used , which ignores the Mach number effect as well as the shear constant and the Chapman–Rubesin parameter of the boundary layer prior to separation. Subsequently, Egorov et al.…”

Section: Introductionmentioning

confidence: 99%

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Hypersonic compression corner flow with large separated regions

Gai

Khraibut

2019

J. Fluid Mech.

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The structure of large-scale hypersonic boundary layer separation and reattachment is studied numerically using a flat plate/compression corner geometry. Apart from verifying the large scale separation characteristics in hypersonic flow, a detailed discussion of secondary separation and fragmentation into multiple vortices embedded within the main recirculation region is presented. The unique relation between the second minimum in shear stress and the scaled angle is highlighted in the context of the reverse flow singularity of Smith (Proc. R. Soc. Lond. A, vol. A420, 1988, pp. 21–52) and it appears that for a small wall temperature ratio, such a singularity is unlikely. It is shown that the size of the separation can be estimated in terms of Burggraf’s expression based on asymptotic theory.

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Section: The Compression Corner Geometrymentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Hypersonic compression corner flow with large separated regions

Gai

Khraibut

2019

J. Fluid Mech.

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“…The first, near the wall, is a rotational viscous subsonic region which is most sensitive to disturbances, the second is a main inviscid rotational region and the third is an inviscid irrotational outer region, which is most resistive to disturbances. Interaction between these decks (Stewartson 1974) has been shown to be dependent on wall temperature by a number of authors such as Brown, Cheng & Lee (1990), Seddougui, Bowles & Smith (1991), Kerimbekov, Ruban & Walker (1994), Cassel, Ruban & Walker (1995), Cassel, Ruban & Walker (1996), Neiland, Sokolov & Shvedchenko (2009) and Shvedchenko (2009).…”

Section: Introductionmentioning

confidence: 99%

Numerical study of bluntness effects on laminar leading edge separation in hypersonic flow

Khraibut¹,

Gai²,

Neely³

2019

J. Fluid Mech.

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Bluntness effects on laminar hypersonic leading edge separation are investigated numerically at Mach number $M\approx 10$, unit Reynolds number $Re=1.3\times 10^{6}~\text{m}^{-1}$, specific enthalpy $h_{o}=3.1~\text{MJ}~\text{kg}^{-1}$ and wall-to-stagnation temperature ratio $T_{w}/T_{o}=0.1$. Such effects are important from an experimental point of view and because bluntness can affect a separated flow favourably or adversely. In this study, two blunt leading edge cases of small radius ($15~\unicode[STIX]{x03BC}\text{m}$) and large radius ($100~\unicode[STIX]{x03BC}\text{m}$) are investigated. A comparison with the idealised sharp leading edge case is also given. General flow features and surface parameters such as the shear stress, pressure and heat flux are presented and analysed. The results have also been interpreted in terms of Cheng’s displacement-bluntness similitude parameter affecting the size of separation. Previous experiments by Holden delineated small and large bluntness effects based on Cheng’s parameter and considering small to moderate separated regions. In this study, leading edge separation was found to suppress the favourable effect of bluntness in delaying separation. Bluntness, furthermore, seemed to promote the appearance of secondary vortices within a main separated region. Analysis of reverse flow boundary layer profiles such as velocity, pressure and temperature is also given. It is shown that bluntness accentuates large transverse gradients. This in turn adversely effects the reverse flow boundary layer leading to the appearance of secondary vortices.

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Numerical investigation of a Mach 6 hypersonic laminar flow on two-dimensional cold-wall compression corners with controlled surface roughness

Giuseppe

Stemmer

2022

International Journal of Heat and Fluid Flow

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About the Secondary Separation at Supersonic Flow Over a Compression Ramp

Cited by 20 publications

References 0 publications

Hypersonic compression corner flow with large separated regions

Hypersonic compression corner flow with large separated regions

Numerical study of bluntness effects on laminar leading edge separation in hypersonic flow

Numerical investigation of a Mach 6 hypersonic laminar flow on two-dimensional cold-wall compression corners with controlled surface roughness

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