SUPERSONIC FLOW SEPARATION ON A BACKWARD FACING STEP.

SUPERSONIC FLOW SEPARATION ON A BACKWARD FACING STEP.
Author:
Publisher:
Total Pages: 42
Release: 1966
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The paper describes an experimental survey of flow separation on backward facing steps having different heights at a Mach number of 2.4. Reattachment and critical points are found for three regimes, laminar, transitional, and turbulent. Reattachment occurs at a point where the pressure is 35% of the free stream value for turbulent flow, and 60% of this value in the laminar case. The length of the free shear layer is found to be one-half that of the separating streamline, a result which emphasizes the importance of the reattachment region. The flow downstream of the critical point is found to be relatively independent of the base flow. Disturbances in the spanwise direction are always observed in laminar flow but do not affect the base pressure.

Supersonic Separated Flow Downstream of a Backward Facing Step

Supersonic Separated Flow Downstream of a Backward Facing Step
Author: Donald R. Crawford
Publisher:
Total Pages: 166
Release: 1967
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The method of integral relations is applied to the study of the viscous separated flow field downstream of a backward facing step in laminar supersonic flow. The boundary layer equations are reduced to a set of coupled ordinary differential equations in a formulation which incorporates a two parameter velocity profile. The neighborhood of the corner and the reattachment point are examined in detail, taking into account the proper interaction between the viscous and inviscid flow. The complete flow field in these regions is found from the analyses of the limiting forms of the equations. In particular, it is found that the pressure gradient and thickness of the boundary layer at the reattachment point are related and cannot be arbitrarily specified. (Author).

LAMINAR SEPARATION IN SUPERSONIC FLOW.

LAMINAR SEPARATION IN SUPERSONIC FLOW.
Author: Jean J. Ginoux
Publisher:
Total Pages: 75
Release: 1964
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Detailed experimental investigations were made at a Mach number of 2.21 of laminar flows over ramps, backward facing steps and swept back wings. Large spanwise variations of the heat transfer coefficient (h) were measured, with two different techniques, in the reattachment region of the flow over a backward facing step and were related to streamwise vortices present in the laminar boundary layer. Peaks in h much larger than the turbulent value were measured. By comparing spanwise total head and heat transfer rate distributions, Reynolds analogy was found to apply quantitatively for reattaching flows with streamwise vortices. The effect of free-stream Reynolds number and of leading edge sweep, accuracy of machining, thickness and bevel angle on the intensity of streamwise vortices present in the boundary layer on swept back wings was investigated. Flow separation was detected at the leading edge. A regular pattern of streamwise vortices of small wave length was observed outside of the boundary layer.

Computational Study of Supersonic Flow Over Backward-Facing Steps at High Reynolds Number

Computational Study of Supersonic Flow Over Backward-Facing Steps at High Reynolds Number
Author: Odus R. Burggraf
Publisher:
Total Pages: 56
Release: 1970
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The problem of laminar separated flow over a backward-facing step is solved numerically for the limiting case of infinite Reynolds number. The flow model adopted is that deduced by Batchelor for incompressible flow: an inviscid rotational eddy confined within the recirculation portion of the separated shear layer. It is argued that the reattachment process is essentially inviscid in the limit R approaches infinity, and the flow field in the reattachment zone is computed on this basis. The computed results support Chapman's model of the reattachment process as the correct limit case, to second-order accuracy, as the flow angle entering the reattachment zone approaches zero. For the recirculation zone, the boundary-layer equations are simplified by assuming a constant pressure eddy. The Dorodnitsyn transformation is applied and numerical solutions obtained using an implicit finite-difference scheme. The solutions are carried out from station-to-station in the direction of flow over a complete cycle of recirculation. Iteration yields the unique value of the vorticity in the inviscid layer upstream of separation, including the effects of corner expansion and recirculation on the development of the separated shear layer. (Author).

An Algebraic Turbulence Model for Flow Separation Caused by Forward and Backward Facing Steps

An Algebraic Turbulence Model for Flow Separation Caused by Forward and Backward Facing Steps
Author: James E. Danberg
Publisher:
Total Pages: 34
Release: 1989
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ISBN:

The Baldwin-Lomax algebraic turbulence model is currently widely used in numerical Navier-Stokes codes primarily because it avoids the problems of calculating a boundary layer thickness. However, two of its disadvantages are: 1) it requires the evaluation of a maximum in the moment of vorticity with respect to the surface which is ambiguous under certain conditions and, 2) its applicability to some separated flows is unclear. The basis for the Baldwin-Lomax method is reviewed in detail particularly as it applies to locally separated flows. This leads to a reformulation of the Baldwin-Lomax method. The modification uses a velocity scale, at each separated flow station, which is the difference between the maximum velocity and the minimum velocity (considered negative in separated flows with recirculation regions). The length scale is defined in terms of the ratio of this velocity scale to the maximum vorticity. Other modifications are included which adapt the model to forward and rearward facing step applications. Keywords: Fluid mechanics; Turbulent flow; Forward and backward steps; Separated flow; Supersonic flow; Turbulence modeling; Algebraic model. (JHD).