Assessment of Jet-plate Interaction Noise Using the Lattice Boltzmann Method

Abstract

A numerical investigation of a jet interacting with a flat plate was conducted using a LBM-VLES approach. Simulations were conducted with a round jet under a large flat plate, with jet Mach number 0.3 (ReD = 2.6 × 10 5 ) and 0.5 (ReD = 4.3 × 10 5 ). The aim was to observe the capabilities of the method to investigate jet installation effects. Far-field SPL data were obtained using the Ffowcs-Williams and Hawkings (FW-H) surface integral method with permeable and solid surfaces. The position of the plate relative to the nozzle was varied and the effects on the far-field noise were observed. Results showed good agreement with experimental data, up to StD = 2. Noise data obtained with solid surfaces suggested that the plate pressure field contained the main information of the installation effect. Results highlighted the potentialities of the code for investigating the noise generation from jetsurface interaction.

Noise Amplification Effects due to Jet-Surface Interaction

“…A validation study for the isolated SMC000 jet flow has been also accomplished [14]. For an installed jet, computations were performed by Silva et al [22]. The results, in terms of far-field noise spectra, showed a good agreement with experimental data, indicating the capability of the methodology to accurately predict the jet-installation noise.…”

“…The information on the fluctuations of flow properties is stored in this surface, where the integration is performed for the far-field noise propagation. This methodology allows for the inclusion of all noise sources placed inside the surface, such as the dipoles on the plate and the quadrupoles in the jet [22]. The characteristics of the FWH surface are included in Section II.C.…”

Simulation of Isolated and Installed Jet Noise at Mach = 0.9: Influence of Numerical Mesh and Physical Insights

“…Second, the flat plate reflects the pressure waves and act as a shielding. The classical methodology to compute such a configuration is to solve the propagation of the acoustic waves around the plate in the CFD simulation, the coupling with an integral method being performed outside of the jet-plate region in the uniform, free-field flow (Tyacke et al 2019;Rego et al 2020;Bondarenko et al 2012;Angelino et al 2018Angelino et al , 2019Stich et al 2019;Wang et al 2020;Silva et al 2015). Such an approach may however be very expensive, in particular when the extent of the plate is large.…”

“…With this approach the far-field pressure fluctuations are reconstructed from the unsteady flow fields on a porous surface encompassing the noise sources for a very affordable numerical cost. This methodology remains valid in the presence of a wing and has been used by several authors (Tyacke et al 2019;Bondarenko et al 2012;Angelino et al 2018Angelino et al , 2019Stich et al 2019;Wang et al 2020;Silva et al 2015;Rego et al 2020). The numerical cost of the CFD simulation however becomes important when the wing span is large because all acoustic effects, including the propagation of acoustic waves up to the wing extremities, need to be accurately captured during the flow simulation.…”

Numerical Investigation on Vortex‐Structure Interaction Generating Aerodynamic Noises for Rod‐Airfoil Models

“…In particular, the Lattice-Boltzmann-Method (LBM) has shown being a very promising technique for far field aeroacoustic prediction (Benjamin Duda, Ehab Fares, 2017), such as LAGOON landing-gear configuration [9] and Jet-plate interaction noise [10]. Currently the hybrid method is the most popular method which predicts the sound by combination of the computation fluid dynamics solvers for acoustic source identification [11][12][13] and the Lighthill's analogy theory for sound propagation [14].…”