Strip blowing from a wedge at hypersonic speeds

Messiter, A. F.; Matarrese, M. D.

doi:10.2514/3.12372

Cited by 4 publications

(2 citation statements)

References 11 publications

(18 reference statements)

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“…Hypersonic flows with strong wall cooling are of considerable current interest owing to the necessity of maintaining the thermal integrity of future hypersonic vehicles (Walberg 1991 ; Townend 1991). In general, complex multi-layer phenomena can occur in this environment, especially when boundary-layer separation develops ; recently Messiter, Matarrese & Adamson (1991) have studied the case of strip blowing on a wedge and Brown, Cheng & Lee (1990) have investigated compressive free interactions and the compression ramp with strong wall cooling. The present study is also concerned with the compression ramp and the relation to the work of Brown et al (1990) will be discussed subsequently.…”

Section: R M Kerimbekov a I Rubun And J D A Walkermentioning

confidence: 99%

Hypersonic boundary-layer separation on a cold wall

1994

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An asymptotic theory of laminar hypersonic boundary-layer separation for large Reynolds number is described for situations when the surface temperature is small compared with the stagnation temperature of the inviscid external gas flow. The interactive boundary-layer structure near separation is described by well-known tripledeck concepts but, in contrast to the usual situation, the displacement thickness associated with the viscous sublayer is too small to influence the external pressure distribution (to leading order) for sufficiently small wall temperature. The present interaction takes place between the main part of the boundary layer and the external flow and may be described as inviscid–inviscid. The flow in the viscous sublayer is governed by the classical boundary-layer equations and the solution develops a singularity at the separation point. A main objective of this study is to show how the singularity may be removed in different circumstances.

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Section: R M Kerimbekov a I Rubun And J D A Walkermentioning

confidence: 99%

Hypersonic boundary-layer separation on a cold wall

1994

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“…Keeping this in mind Neiland (1973) demonstrated that the main part of the boundary layer starts to play a significant role in the interaction process when the wall temperature is reduced to a certain level. Later, different aspects of the theory of hypersonic boundary-layer separation on a cold wall including flow regimes with inviscid-inviscid interaction were studied by Neiland & Sokolov (1975), Brown, Cheng & Lee (1990), Messiter, Matarrese & Adamson (1991) and Kerimbekov, Ruban & Walker (1994).…”

Section: Discussionmentioning

confidence: 99%

On laminar separation at a corner point in transonic flow

Ruban

Türkyılmaz

2000

J. Fluid Mech.

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The separation of the laminar boundary layer from a convex corner on a rigid body contour in transonic flow is studied based on the asymptotic analysis of the Navier–Stokes equations at large values of the Reynolds number. It is shown that the flow in a small vicinity of the separation point is governed, as usual, by strong interaction between the boundary layer and the inviscid part of the flow. Outside the interaction region the Kármán–Guderley equation describing transonic inviscid flow admits a self-similar solution with the pressure on the body surface being proportional to the cubic root of the distance from the separation point. Analysis of the boundary layer driven by this pressure shows that as the interaction region is approached the boundary layer splits into two parts: the near-wall viscous sublayer and the main body of the boundary layer where the flow is locally inviscid. It is interesting that contrary to what happens in subsonic and supersonic flows, the displacement effect of the boundary layer is primarily due to the inviscid part. The contribution of the viscous sublayer proves to be negligible to the leading order. Consequently, the flow in the interaction region is governed by the inviscid–inviscid interaction. To describe this flow one needs to solve the Kármán–Guderley equation for the potential flow region outside the boundary layer; the solution in the main part of the boundary layer was found in an analytical form, thanks to which the interaction between the boundary layer and external flow can be expressed via the corresponding boundary condition for the Kármán–Guderley equation. Formulation of the interaction problem involves one similarity parameter which in essence is the Kármán–Guderley parameter suitably modified for the flow at hand. The solution of the interaction problem has been constructed numerically.

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The principle of pressure decomposed for flow over a flat plate and its application on the magnetic fluids

Yamaguchi

Niu

2010

Physics Procedia

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Strip blowing from a wedge at hypersonic speeds

Cited by 4 publications

References 11 publications

Hypersonic boundary-layer separation on a cold wall

Hypersonic boundary-layer separation on a cold wall

On laminar separation at a corner point in transonic flow

The principle of pressure decomposed for flow over a flat plate and its application on the magnetic fluids

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