Energy separation in a compressible vortex street

Rona, Aldo; Bennett, W.P.

doi:10.2514/6.2001-601

Cited by 2 publications

(6 citation statements)

References 8 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The variation in magnitude and location of the total temperature distribution is linked to different vortex shedding characteristics between the experiment and computation. This link between the non-uniform total temperature field and the vortex shedding characteristics is indicated in previous work for circular cylinders 4,8,9 and turbine blades.…”

Section: Total Temperature Fieldmentioning

confidence: 98%

“…The numerical model cylinder diameter differs from previous work 8,9 for dynamic similarity with the experimental program. A cold flow of Mach number M = 0.6 approaches the cylinder.…”

Section: Flow Conditionsmentioning

confidence: 99%

“…American Institute of Aeronautics and Astronautics work 8,9 to be a predominant source of entropy production in the near wake region. The influence of the shearing flow is still identifiable to a lesser degree in the numerical prediction at the current downstream position of six cylinder diameters, Fig 7(b).…”

mentioning

confidence: 99%

“…The numerical model is time marched from the initial uniform distribution to a quasi-stationary vortex shedding regime using the inviscid numerical method detailed in Rona & Bennett. 8 The development of the quasi-stationary vortex shedding inviscid flow prediction is detailed in Rona & Bennett. 8 The quasistationary inviscid flow prediction is then used to prime the turbulent computation.…”

mentioning

confidence: 99%

“…8 The development of the quasi-stationary vortex shedding inviscid flow prediction is detailed in Rona & Bennett. 8 The quasistationary inviscid flow prediction is then used to prime the turbulent computation. for the short-time averaged kinetic energy production k ∞ , and dissipation rate ω ∞ are defined throughout the computational domain.…”

mentioning

confidence: 99%

See 4 more Smart Citations

Experimental and Numerical Study of the Non-uniform Total Temperature in a Turbulent Mach 0.6 Vortex Street

Bennett

Rona

Ackerman

et al. 2003

41st Aerospace Sciences Meeting and Exhibit

View full text Add to dashboard Cite

NOMENCLATURE ABSTRACTThis work investigates the non-uniform total temperature and total pressure downstream of a circular cylinder in transonic flow. At Mach 0.6 shock induced separation of the flow occurs from the surface of the cylinder. The unsteady shear layers roll up into vortices that are shed from the cylinder forming a von Kármán vortex street of convecting vortices. An experimental investigation of the vortex street is carried out at a distance of six cylinder diameters downstream. Time resolved total temperature measurements reveal the presence of localised 'hot spots' of increased total temperature at the edges of the wake and localised * Research Student.'cold spots' of decreased total temperature along the centre of the wake. The experimental measurements are compared against a concurrent numerical study using a time accurate numerical model with turbulence closure. The numerical model also captures the nonuniform total temperature and total pressure distribution downstream of the cylinder. The non-uniform total temperature and total pressure distribution is shown to be a source of entropy production. Comparison of the total temperature and total pressure distribution highlights the influence of the boundary layer development and separation characteristics on the vortex shedding and energy separation processes. This emphasizes the importance of including the effects of turbulence and boundary layer development in numerical studies of the energy separation downstream of circular cylinders.

show abstract

Section: Total Temperature Fieldmentioning

confidence: 98%

“…The numerical model cylinder diameter differs from previous work 8,9 for dynamic similarity with the experimental program. A cold flow of Mach number M = 0.6 approaches the cylinder.…”

Section: Flow Conditionsmentioning

confidence: 99%

mentioning

confidence: 99%

mentioning

confidence: 99%

mentioning

confidence: 99%

See 3 more Smart Citations

Experimental and Numerical Study of the Non-uniform Total Temperature in a Turbulent Mach 0.6 Vortex Street

Bennett

Rona

Ackerman

et al. 2003

41st Aerospace Sciences Meeting and Exhibit

View full text Add to dashboard Cite

show abstract

An Aeroacoustic Numerical Model of the Transonic Flow Past a Sphere

Duggins

Angelino

Rona

2022

28th AIAA/CEAS Aeroacoustics 2022 Conference

View full text Add to dashboard Cite

Transonic flow past a sphere is investigated by Large Eddy Simulations. The Reynolds number based on the diameter of the sphere and on the free-stream quantities is 1000, while the free-stream Mach number is 0.9. This regime generates a weakly supersonic flow behind the sphere, with a stationary compression wave a few diameters downstream which traverses the developing turbulent wake. The focus of this study is the sound radiated from the wake turbulent structures and their interaction with the stationary compression wave. This direct aeroacoustic computation shows a spiral pressure wave radiating from the base flow precessing about the free-stream unit vector passing through the centre of the sphere. The main acoustically active region is the stationary compression wave-wake interaction one. The localised supersonic flow over the sphere prevents the upstream radiation in a cone of silence type effect within a narrow solid angle upstream of the sphere, which could be exploited for passive noise control.

show abstract

Energy separation in a compressible vortex street

Cited by 2 publications

References 8 publications

Experimental and Numerical Study of the Non-uniform Total Temperature in a Turbulent Mach 0.6 Vortex Street

Experimental and Numerical Study of the Non-uniform Total Temperature in a Turbulent Mach 0.6 Vortex Street

An Aeroacoustic Numerical Model of the Transonic Flow Past a Sphere

Contact Info

Product

Resources

About