Boundary-layer separation on a cooled body and interaction with a hypersonic flow

Neiland, V. Ya.

doi:10.1007/bf01014269

Cited by 13 publications

(23 citation statements)

References 6 publications

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“…At the same time, this does not mean that the interaction process remains unaffected; indeed, along with the reduction in the displacement thickness contribution due to the viscous sublayer, there is a corresponding rise in the relative contribution from the main deck and both become important to leading order once the wall temperature is sufficiently low. As shown by Neiland (1973), the displacement thickness attributable to the main deck is proportional to the pressure rise induced by the boundary layer. If the average Mach number M across the upstream boundary layer is less than one, a pressure increase leads to boundary-layer thickening in the interaction region; on the other hand, if A ?…”

Section: Introductionmentioning

confidence: 96%

“…Triple-deck analysis has subsequently been applied to many problems spanning the full range of flow speeds from subsonic to hypersonic. The formulation was subsequently extended to hypersonic flow with significant wall cooling by Neiland (1973) and later by Brown, Cheng & Lee (1990). Wall cooling is often necessary in hypersonic flow applications in order to combat the high temperatures generated near the surface (Towend 1991 ;Walberg 1991).…”

Section: Introductionmentioning

confidence: 99%

“…> 1, a pressure increase leads to a decrease in the boundary-layer thickness. The former case was referred to as subcritical and the latter as supercritical by Neiland (1973) because of an analogous behaviour for subsonic and supersonic mainstream flows, respectively.…”

Section: Introductionmentioning

confidence: 99%

“…The hypersonic formulation with wall cooling used in the present investigation follows the seminal work of Neiland (1973), wherein the terms 'supercritical', 'transcritical' and 'subcritical' connoted the state of the upstream boundary layer for 192 K . W Cassel, A .…”

Section: Introductionmentioning

confidence: 99%

“…In the Appendix, a brief comparison of the two approaches is given. In this paper, Neiland's (1973) terminology will be used throughout. The present results for supercritical boundary layers compare very well with those of Brown et al (1990) who sought steady solutions in regime 2, but did not consider the subcritical case.…”

Section: Introductionmentioning

confidence: 99%

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The influence of wall cooling on hypersonic boundary-layer separation and stability

1996

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The effect of wall cooling on hypersonic boundary-layer separation near a compression ramp is considered. Two cases are identified corresponding to the value of the average Mach number $\overline{M}$ across the upstream boundary layer approaching the compression ramp. The flow is referred to as supercritical for $\overline > 1$ and subcritical for $\overline{M} < 1$. The interaction is described by triple-deck theory, and numerical results are given for both cases for various ramp angles and levels of wall cooling. The effect of wall cooling on the absolute instability described recently by Cassel, Ruban & Walker (1995) for an uncooled wall is of particular interest; a stabilizing effect is observed for supercritical boundary layers, but a strong destabilizing influence occurs in the subcritical case. Wall cooling also influences the location and size of the separated region. For supercritical flow, progressive wall cooling reduces the size of the recirculating-flow region, the separation point moves downstream, and upstream influence is diminished. In contrast for the subcritical case downstream influence is reduced with increased cooling. In either situation, a sufficient level of wall cooling eliminates separation altogether for the ramp angles considered. The present numerical results closely confirm the strong wall cooling theory of Kerimbekov, Ruban & Walker (1994).

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Section: Introductionmentioning

confidence: 96%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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The influence of wall cooling on hypersonic boundary-layer separation and stability

1996

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Bibliography**References to the books by Russian and other non-English-speaking authors are given in accordance with their English translations, if there are any and they are known to the authors or the translator. As for the papers from Russian scientific journals cited in this book, most of them were published in the following three journals: Prikladnaya Matematika i Mekhanika, Izvestiya Akademii Nauk, ser. Mekhanika Zhidkosti i Gaza, and Zhurnal Prikladnoi Meknaniki i Tekhnicheskoi Fiziki. All the three

2008

Asymptotic Theory of Supersonic Viscous Gas Flows

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Laminar hypersonic leading edge separation – a numerical study

Khraibut¹,

Gai²,

Brown³

et al. 2017

J. Fluid Mech.

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This paper describes laminar hypersonic leading edge separation. Such a configuration of separated flow was originally studied by Chapman et al. (NACA Tech. Rep. 1356, 1958) at supersonic Mach numbers as it is particularly amenable to theoretical analysis and assumes no pre-existing boundary layer. It can be considered as a limiting case of much studied generic configurations such as separation at a compression corner and separated flow behind a base. A numerical investigation is described using a compressible Navier–Stokes solver assuming perfect gas air, no slip boundary condition and a non-catalytic surface. A moderate enthalpy flow of $3.1\times 10^{6}~\text{J}~\text{kg}^{-1}$ with a unit Reynolds number of $1.34\times 10^{6}~\text{ m}^{-1}$ and a Mach number of 9.66 was considered. The resulting separated flow is analysed in the context of viscous–inviscid interaction and interpreted in terms of ‘triple-deck’ concepts. Particular emphasis is given to wall temperature effects. The effects of strong to moderate wall cooling on flow in the separated region as well as on processes of separation, reattachment and separation length, are highlighted. The numerical simulations have also shown the existence of a secondary eddy embedded within the primary recirculation region, with its size, shape and position, being strongly affected by the wall temperature.

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Boundary-layer separation on a cooled body and interaction with a hypersonic flow

Cited by 13 publications

References 6 publications

The influence of wall cooling on hypersonic boundary-layer separation and stability

The influence of wall cooling on hypersonic boundary-layer separation and stability

Laminar hypersonic leading edge separation – a numerical study

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