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A series of Wall Modelled Large Eddy Simulations (WMLES) based on the high-resolution CABARET method accelerated on Graphics Processing Units (GPUs) are performed for conditions of the SYMPHONY installed jet noise experiment. The SYMPHONY case corresponds to a short-cowl co-axial jet flow with a pylon installed under a wing with a flap and a fuselage body. The jet is heated and includes the flight stream effect. Before applying it to the installed jet of industrial-type complexity, the wall grid resolution, the local grid refinement, and the acoustic integration surface requirements of GPU-CABARET are systematically validated in two benchmark cases. The first benchmark case corresponds to the NASA wall-mounted hump problem, and the second case corresponds to the NASA installed jet configuration. In the second case, the GPU-CABARET solutions coupled with the Ffowcs Williams and Hawkings (FW-H) method based on multiple penetrable control surfaces are compared both with the NASA data, and the medium and fine grid solutions of the Latice Boltzman Method (LBM) from the literature, and show good agreement. The computational performance of GPU-CABARET and LBM is compared. After validation on the two NASA benchmark problems, the GPU-CABARET coupled with the FW-H method is applied to the SYMPHONY jet case. A range of LES grids from 80 million to 243 million cells is considered, and the effects of jet installation and flight stream on jet flow development are systematically analysed. As a cross-verification test, the fine-grid LES solution of the installed SYMPHONY jet for the sectional pressure coefficient on the wing-flap surface close to the jet is shown to be in good agreement with the reference Reynolds Averaged Navier-Stokes solution. The noise spectra solutions of the GPU-CABARET/FW-H method are shown to be within 2–3 dB from the experiment for most angles and frequencies, but there are also a few discrepancies. The effects of jet installation, flight stream, and shielding by the wing and the fuselage of the SYMPHONY jet are analysed. Additional LES calculations of the equivalent unheated single-stream installed jet are performed for a range of jet Mach numbers to obtain further insights into the effective jet installation noise mechanism in the SYMPHONY experiment. The extracted jet noise exponents for a few representative far-field microphone locations are compared with the available data in the literature.
Markesteijn et al. (Mon,) studied this question.