Browsing by Author "Tucker, Paul"

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    LES study of noise and its sources of closely installed jets
    (AIAA, 2022-06-13) Wang, Zhong-Nan; Proenca, Anderson; Lawrence, Jack; Tucker, Paul; Self, Rod
    When a jet is closely installed under a solid surface, turbulent jet plume is modified. Two levels of jet-plate interactions are present. In addition to linear evanescent instability wave scattered by the plate trailing edge, nonlinear jet turbulence strongly interacts with the plate underneath surface. Both of the interactions could lead to far-field noise change but with different mechanisms. Large-Eddy Simulation (LES) has been performed on two installed jets and one baseline isolated jet to investigate the noise generation mechanisms for this closely installed jet. The distance between jet and plate surface is adjusted for the two installed jets so that strong hydrodynamic interaction is only present in one of the configurations. Far-field noise, computed using Ffowcs Williams-Hawkings (FW-H) equations, is compared for the two installed jets to show the effect of close installation. The near-field sound sources are exmined by analysing quadrupole souces of turbulent mixing and dipole sources of unsteady plate surface loading.
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    Wall-resolved large eddy simulation for aeroengine aeroacoustic investigation
    (Cambridge University Press, 2017-06-22) Lin, Yujing; Vadlamani, Rao; Savill, Mark; Tucker, Paul
    The work presented here forms part of a larger project on Large-Eddy Simulation (LES) of aeroengine aeroacoustic interactions. In this paper, we concentrate on LES of near-field flow over an isolated NACA0012 aerofoil at zero angle-of-attack and a chord based Reynolds number of Rec = 2 × 105. A wall-resolved compressible Numerical Large Eddy Simulation (NLES) approach is employed to resolve streak-like structures in the near-wall flow regions. The calculated unsteady pressure/velocity field will be imported into an analyticallybased scheme for far-field trailing-edge noise prediction later. The boundary-layer mean and root-mean-square (rms) velocity profiles, the surface pressure fluctuation over the aerofoil, and the wake flow development are compared with experimental data and previous computational simulations in our research group. It is found that the results from the wall-resolved compressible NLES are very encouraging as they correlate well with test data. The main features of the wall-resolved compressible NLES, as well as the advantages of such compressible NLES over previous incompressible LES performed in our research group, are also discussed. This paper will be presented at the ISABE 2017 Conference, 5-8 September 2017, Manchester, UK.