Large-eddy simulation of twin impinging jets in cross-flow

Li, Q; Page, Gary J.; McGuirk, James J.

doi:10.1017/s0001924000004450

Cited by 25 publications

(19 citation statements)

References 19 publications

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“…The computational code used here (DELTA) was developed at Loughborough University and has previously been applied to LES of impinging jets in crossflow (Li et al [39]), to LES of subsonic jet aeroacoustics [40], and to LES of a full aircraft [41], also to the closely related problem to that considered here of LES of crossflow vortices on an infinite swept wing controlled by suction (Mistry et al [42]). The code adopts a cell--centred, finite--volume, pressure--based method on a multi--block structured grid.…”

Section: Les Codementioning

confidence: 99%

Simulation of Receptivity and Induced Transition From Discrete Roughness Elements

Mistry

Page

McGuirk

2015

Flow Turbulence Combust

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The WALE sub--grid stress (SGS) model was adopted for application to transitional flows, since it allows the SGS viscosity to vanish in laminar regions and in the innermost region of the boundary layer when transition begins. Simulations were carried out for two spanwise wavelengths: λ = 12mm (critical) and λ = 6mm (control), and for roughness heights (k) from 12µm to 42µm. The base flow considered was an ASU (67)--0315 aerofoil with 45 0 sweep at --2.9 0 incidence and with onset flow at a chord--based Reynolds number Re c = 2.4x10 6 . For λ = 12mm results showed, in accord with the experimental data, that the disturbance amplitude growth rate was linear for k = 12µm and 24µm, but the growth rate was decreased for k = 36µm. Receptivity to λ = 6mm roughness showed equally good agreement with experiments, indicating that this mode disappeared after a short distance to be replaced by a critical wavelength mode. Analysis of the development of modal disturbance amplitudes with downstream distance showed regions of linear, non--linear, saturation, and secondary instability behaviour. Examination of breakdown to turbulence revealed two possible routes: the first was 2D--like transition (probably Tollmien--Schlichting waves even in the presence of crossflow vortices) when transition occurred beyond the pressure minimum; the second was a classical crossflow vortex secondary instability, leading to the formation of a turbulent wedge.

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Section: Les Codementioning

confidence: 99%

Simulation of Receptivity and Induced Transition From Discrete Roughness Elements

Mistry

Page

McGuirk

2015

Flow Turbulence Combust

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“…flowfields such as multiple impinging jets (6,7) have already appeared. The Large Eddy Simulation CFD methodology is much more likely to be able to predict accurately both the mean and unsteady components of the flow that are so important in determining ground effect flow characteristics such as hot gas ingestion.…”

Section: Governing Equationsmentioning

confidence: 99%

“…The flow condition corresponding to a velocity ratio R = V J /U C (impinging jet vertical velocity divided by crossflow axial velocity) of 24 and an impingement height of 7 D j gave intermittent ingestion of the jet fluid into the intake and was chosen for simulation. The jet Reynolds number based on exit velocity and nozzle diameter was 40,000; only a brief description of the results is provided here, more details may be found in Li et al (7) . An unstructured mesh of ~1⋅8 million cells was generated, as shown in Fig.…”

Section: Twin Impinging Jet With Intake In Cross-flowmentioning

confidence: 99%

Large Eddy Simulation of a complete Harrier aircraft in ground effect

Page¹,

McGuirk²

2009

Aeronaut. j.

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This paper aims to demonstrate the viability of using the large eddy simulation (LES) CFD methodology to model a representative, complete STOVL aircraft geometry at touch down. The flowfield beneath such a jet-borne vertical landing aircraft is inherently unsteady. Hence, it is argued in the present work that the LES technique is the most suitable tool to predict both the mean flow and unsteady fluctuations, and, with further development and validation testing, this approach could be a replacement, and certainly a complementary aid, to expensive rig programmes. The numerical method uses a compressible solver on a mixed element unstructured mesh. Examination of instantaneous flowfield predictions from these LES calculations indicate close similarity with many flow features identified from ground effect flow visualisations, which are well known to be difficult to model using RANS-based CFD. Whilst significant further work needs to be carried out, these calculations show that LES could be a practical tool to model , for example, Hot Gas Ingestion for the Joint Strike Fighter aircraft.

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“…The head wind causes the flow along the ground to deflect upwards creating a vortex back towards the intakes. This will increase the intake air temperature and less content of oxygen, potentially leading to compressor stall and causing a dramatic engine thrust loss [1,2].…”

Section: Introductionmentioning

confidence: 99%

A CFD Study of Twin Impinging Jets in a Cross-Flow

Ostheimer¹

2012

TONUMJ

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A very complicated three-dimensional (3D) flow field is generated beneath a Vertical/Short Take-Off and Landing (VSTOL) aircraft when it is operated near the ground. This flow field can be represented by the configuration of twin impinging jets along the spanwise direction in a cross-flow. This paper describes a Computational Fluid Dynamics (CFD) study of this flow using the Reynolds Averaged Navier-Stokes (RANS) approach with a Reynolds Stress Model (RSM). The use of an RSM potentially offers a compromise between the computational efficiency of a two equation turbulence model and accuracy closer to that of Large Eddy Simulation (LES) although it will not be as accurate as LES. The current numerical results are validated against experimental data and the mean velocity profiles are reasonably well predicted by both the standard k-model and the RSM with slightly better prediction by the RSM. However, the Reynolds stress prediction by the RSM is poor compared with the experimental data, indicating that to capture the detailed unsteady flow features an LES is needed.

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Large-eddy simulation of twin impinging jets in cross-flow

Cited by 25 publications

References 19 publications

Simulation of Receptivity and Induced Transition From Discrete Roughness Elements

Simulation of Receptivity and Induced Transition From Discrete Roughness Elements

Large Eddy Simulation of a complete Harrier aircraft in ground effect

A CFD Study of Twin Impinging Jets in a Cross-Flow

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