Near wake flow field measurements.

Pallone, A.; Todisco, A.

doi:10.2514/3.3317

Cited by 35 publications

(3 citation statements)

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“…The wake geometry so calculated agreed precisely with experimental results' 21 ', for Re Xjl = 2x 10*, and the calculated and experimental total temperature variations on the wake axis were in good quantitative agreement. The axial pressure distribution exhibited the expected rise towards the rear stagnation point, and also the smaller rise at the centre of the base wall.…”

Section: The Inviscid Expansion Methods and Overall Near Wake Solutionssupporting

confidence: 77%

“…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%

“…The near wake is divided into three sub-regions: the vortical outer flow, the thin viscous layer above the DSL, and the recirculation region. Numerical solutions were obtained which again enabled comparison with the wedge results of Todisco and Pallone (21) .…”

Section: The Inviscid Expansion Methods and Overall Near Wake Solutionsmentioning

confidence: 99%

See 2 more Smart Citations

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 Solutionssupporting

confidence: 77%

Section: The Inviscid Expansion Methods and Overall Near Wake Solutionsmentioning

confidence: 99%