Compressible Free Shear Layer With Finite Initial Thickness

Baum, Eric; Denison, M. R.

doi:10.2514/3.1535

Cited by 74 publications

(7 citation statements)

References 9 publications

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“…An extension of this work was made by Weiss and Weinbaum' 19 ', who carried out an analysis of the expansion and separation of a hypersonic boundary layer at the shoulder of a 10° semi-angle wedge at Af, =16, Re^ ,~10 5 , the conditions of an experiment by Todisco and Pallone' 21 '. The free shear layer solutions which neglect reflected expansion wave phenomena would in this case overpredict the distance from the base to the rear stagnation point by at least a factor of ten.…”

Section: The Inviscid Expansion Methods and Overall Near Wake Solutionsmentioning

confidence: 99%

“…This solution applies only to that portion of the base flow in which recirculating fluid is being entrained by shear stresses, but despite the many ad hoc assumptions of the model, it was reasonably successful in predicting base pressures in high Reynolds number, low supersonic Mach number conditions. A non-similar shear layer solution was obtained by Denison and Baum (5) , using a finite-difference method within the framework of Chapman's model, with a nonzero boundary-layer thickness. The starting point was a Blasius velocity profile, and for large distances downstream, the profiles approached the Chapman distribution.…”

Section: Free Shear Layer Solutionsmentioning

confidence: 99%

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A Survey of Hypersonic Near Wake Studies

Crane

1969

Aeronaut. j.

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The complicated time-dependent flow in the wake of a blunt based body at low speeds is a well known phenomenon, but drastic changes in the wake structure occur as speeds increase. Somewhere in the transonic regime, the periodic vortex shedding ceases, and at supersonic Mach numbers a steady flow pattern is established. The boundary layer on the body separates to form a free shear layer, the two layers from opposite sides of the body meeting at the so-called neck of the wake. Downstream of this point, the viscous wake persists for many hundreds of body diameters, and the term “far wake” is usually taken to refer to downstream distances greater than about ten body diameters. The neck of a hypersonic wake occurs typically one or two diameters from the base, and marks the downstream end of what is often known as the base flow region; this region includes a low speed, recirculating flow bounded by the shear layers and the base wall. Between the base and somewhere a few body diameters beyond the neck, the flow field is known as the near wake, and forms the subject of this survey.

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Section: The Inviscid Expansion Methods and Overall Near Wake Solutionsmentioning

confidence: 99%

Section: Free Shear Layer Solutionsmentioning

confidence: 99%

A Survey of Hypersonic Near Wake Studies

Crane

1969

Aeronaut. j.

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“…If the case of a free layer is relatively clear when the flow is laminar {see, for instance, ref. 18), it becomes a little more involved when the flow is turbulent. Many papers deal with this question, the first one going back to Gortler' 31 '.…”

Section: Mixing Layermentioning

confidence: 99%

Recent Evolution in Problems and Methods in Aerodynamics

Germain¹

1967

J. R. Aeronaut. Soc.

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The Tenth Lanchester Memorial Lecture “Recent Evolution in Problems and Methods in Aerodynamics” was given before the Society on 11th May 1967 by Professor Paul Germain, Director General of ONERA. The Chair was taken by the President, Mr. M. B. Morgan, CB, MA, CEng, FRAeS.Opening the proceedings the President said that they had had a memorable series of lectures in memory of that great man Lanchester and at many of them it had been a great pleasure to have with them his widow, and his brother Mr. George Lanchester and his wife. They were delighted to have them present that evening.They were fortunate to have as their lecturer Professor Germain, a distinguished French Scientist. It was particularly appropriate that their lecturer should come from France when Franco-British aeronautical ties were already close. Professor Germain was well known to the aeronautical research fraternity. Born at St. Malo in 1920, after graduating in Paris he joined ONERA and later became Professor at, first, Poitiers, then Lille and Paris. Since 1962 he had been Director of ONERA. His theoretical work in the transonic and supersonic aerodynamics fields was well known and they also knew him well personally because he had paid numerous visits to research centres in this country.Professor Germain was France’s National delegate to AGARD and Mr. Morgan knew from personal knowledge the intense interest Professor Germain had taken in that international organisation. He held an Honorary Doctorate from Louvain University, was a Correspondent of the Academy of Sciences, Paris, a Fellow of the American Institute of Aeronautics and Astronautics, a Foreign Honorary Member of the American Academy of Arts and Sciences and a member of the International Academy of Astronautics.

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“…For the case of a very thin boundary layer at separation, and ignoring the cavity vortex system, Chapman (1956) used control volume arguments to predict an upper limit of order 50% for laminar flows, which has been borne out reasonably well by subsequent experiments. In further studies the effect of the initial boundary layer on the development of the laminar free shear layer was considered by, amongst others, Denison & Baum (1963), Kubota & Dewey (1964) and Charwat & Der (1966). Large development distances are required to reach an asymptotic profile, so that in many practical problems the shear layer is likely to be in an early state of non-self-similar growth.…”

Section: Introductionmentioning

confidence: 99%

Experimental and computational study of laminar cavity flows at hypersonic speeds

2001

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This paper presents a combined experimental/computational study of a surface cavity in a low Reynolds number Mach 9 flow. The geometry is based on a body of revolution, which produces highly two-dimensional time-averaged flow for all experimental test cases. A range of cavity length-to-depth ratios, up to a maximum of 8, is investigated. These correspond to ‘closed’ cavity flows, with the free shear layer bridging the entire cavity. For most cases the free shear layer is laminar. However, there is evidence of three-dimensional unsteadiness which is believed to be the consequence of Taylor–Görtler-type vortex formation. The effect of this is first detected on the cavity floor but progressively spreads as the cavity length is increased. For the longest cavities the flow is also influenced by the early stages of laminar–turbulent transition in the free shear layer.

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Compressible Free Shear Layer With Finite Initial Thickness

Cited by 74 publications

References 9 publications

A Survey of Hypersonic Near Wake Studies

A Survey of Hypersonic Near Wake Studies

Recent Evolution in Problems and Methods in Aerodynamics

Experimental and computational study of laminar cavity flows at hypersonic speeds

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