The flow mechanism and acoustics of a supersonic jet impinging on a flat plate is estimated numerically using the code ANSYS FLUENT. The supersonic jet studied is perfectly expanded with a Mach number of 1.5, and it impinges on a flat surface 4 nozzle throat diameters from the jet exit. All turbulence modeling is done using a hybrid RANS/LES technique knows as Delayed Detached Eddy Simulation (DDES). A quasi-periodic transient solution is calculated using the pressure-based coupled solver formulation with the second-order bounded central-upwind spatial discretization and second-order implicit time marching scheme. The acoustic near-field is directly resolved by the Computational Aeroacoustics (CAA) to accurately propagate screech tone waves to a permeable acoustic data surface. The FW-H approach is then applied to calculate far-field acoustics at a specified microphone location. The acoustic field results and mean flow field data compared favorably to available experimental data.
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