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

Published online by Cambridge University Press:  03 February 2016

Q. Li ,
G. J. Page  and
J. J. McGuirk
Q. Li
Affiliation:
Loughborough University, Department of Aeronautical and Automotive Engineering, Leicestershire, UK
G. J. Page
Affiliation:
Loughborough University, Department of Aeronautical and Automotive Engineering, Leicestershire, UK
J. J. McGuirk
Affiliation:
Loughborough University, Department of Aeronautical and Automotive Engineering, Leicestershire, UK
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Abstract

The flow-field beneath a jet-borne vertical landing aircraft is highly complex and unsteady. large-eddy simulation is a suitable tool to predict both the mean flow and unsteady fluctuations. This work aims to evaluate the suitability of LES by applying it to two multiple jet impingement problems: the first is a simple twin impinging jet in cross-flow, while the second includes a circular intake. The numerical method uses a compressible solver on a mixed element unstructured mesh. The smoothing terms in the spatial flux are kept small by the use of a monitor function sensitive to vorticity and divergence. The WALE subgrid scale model is utilised. The simpler jet impingement case shows good agreement with experiment for mean velocity and normal stresses. Analysis of time histories in the jet shear layer and near impingement gives a dominant frequency at a Strouhal number of 0·1, somewhat lower than normally observed in free jets. The jet impingement case with an intake also gives good agreement with experimental velocity measurements, although the expansion of the grid ahead of the jets does reduce the accuracy in this region. Turbulent eddies are observed entering the intake with significant swirl. This is in qualitative agreement with experimental visualisation. The results show that LES could be a suitable tool when applied to multiple jet impingement with realistic aircraft geometry.

Type
Research Article
Information
The Aeronautical Journal , Volume 111 , Issue 1117 , March 2007 , pp. 195 - 206
Copyright
Copyright © Royal Aeronautical Society 2007 

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