Heat transfer investigation on under-expanded supersonic impinging jets

Li, Minghang; Karami, Shahram; Sandberg, Richard D.; Soria, Julio; Ooi, Andrew

doi:10.1016/j.ijheatfluidflow.2023.109132

Cited by 2 publications

(2 citation statements)

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“…While useful in supplementing experiments, CFD simulations have previously not been able to provide high-fidelity results at a tractable cost. However, the advancements in highly scalable high-performance computing (HPC) resources and the development of accurate and computationally efficient CFD solvers render the time right to conduct comprehensive numerical studies of the SIJ configuration, as seen in the recent intensive yet insightful studies in References [16,17], with the latter even including heat transfer effects.…”

Section: Introductionmentioning

confidence: 99%

“…The traditional route to circumvent the limitations of commercial CFD solvers, especially in the academic community, is to develop in-house and purpose-built CFD code [1,5,10,14,17,22]. Not accounting for the time and effort needed for such developments, which are usually daunting and specialized, the cost of in-house CFD solvers is often minimal.…”

Section: Introductionmentioning

confidence: 99%

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Large-Eddy Simulations of a Supersonic Impinging Jet Using OpenFOAM

You,

New,

Chan

2024

Computation

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Supersonic impinging jets are a versatile configuration that can model the compressible flows of cold-spray manufacturing and vertical take-off-and landing strategy. In this work, rhoCentralFoam, solver of the OpenFOAM framework, and a large-eddy simulation formulation were used to simulate an underexpanded supersonic jet of Mach 1.45 and nozzle pressure ratio of 4, impinging on a flat wall situated at 1.5 nozzle diameters away from the jet outlet. Care was taken in the mesh construction to properly capture the characteristic standoff shock and vortical structures. The grid convergence index was evaluated with three meshes of increasing spatial resolution. All meshes can generally be considered as sufficient in terms of results focused on time-averaged values and mean physical properties such as centerline Mach number profile. However, the highest resolution mesh was found to capture fine shear vortical structures and behaviors that are absent in the coarser cases. Therefore, the notion of adequate grid convergence may differ between analyses of time-averaged and transient information, and so should be determined by the user’s intention for conducting the simulations. To guide the selection of mesh resolution, scaling analyses were performed, for which the current rhoCentralFoam solver displays a good weak scaling performance and maintains a linear strong scaling up to 4096 cores (32 nodes) for an approximately 40 million-cell mesh. Due to the internode communication bottlenecks of OpenFOAM and improvements in central processing units, this work recommends, for future scaling analyses, adopting a “cells-per-node” basis over the conventional “cells-per-core” basis, with particular attention to the interconnect speed and architecture used.

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Section: Introductionmentioning

confidence: 99%