Jet noise simulation with realistic nozzle geometries using fully unstructured LES solver

Different jet simulations with realistic nozzle geometries for single and dual jets are performed using the fully unstructured Large Eddy Simulation solver AVBP. Two single jet nozzle geometries from NASA are considered: the Single Metal Chevron 000 which is the base line of the series and the Acoustic Reference Nozzle 2 (ARN2). Both are convergent nozzle but with different section variations. Isothermal Mach 0.9 jets at moderate Reynolds number are simulated using these nozzles. The operating condition corresponds to the set point 7 of Tanna matrix. Grids with different resolutions are used and perturbations are injected in boundary layers to get a fully turbulent mixing layer at the nozzle exit. Apart from a laminar to turbulent transition at the nozzle exit, results show a good agreement with experimental data in terms of aerodynamics and acoustics. A co-axial jet nozzle geometry experimentally studied at the P’ Institute of Poitiers is also simulated. It is a isothermal configuration with a primary jet Mach number of 0.5 and a secondary jet Mach number of 0.35. This low Mach configuration makes it more challenging as the noise level reduces and the acoustic propagation is slower. For the mean flow quantities, an overall good agreement with experimental measurements is obtained. However the flow dynamics is dominated by a strong vortex pairing phenomenon due to the late laminar to turbulent transition of the mixing layers and the discretization of their interactions on the present grid might be unsufficient.

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