Computational aeroacoustic analysis of trailing edge noise: A Direct Numerical Simulation using the Lattice Boltzmann Method

To investigate the mechanisms of wing trailing edge noise the aeroacoustic sound generation by a NACA 0018 has been computed with direct numerical simulations using the Lattice Boltzmann Method. Noise from the straight trailing edge wing is compared with the sound generated by a sawtooth serrated wing, which reduces the noise emission according...

A Symmetry and Dispersion-Relation Preserving High-Order Scheme for Aeroacoustics and Aerodynamics

A new high-order, finite-volume scheme is presented that preserves the symmetry property and the dispersion relation of the convective operator. The scheme is applied to large-eddy simulation of compressible, turbulent flow and to the solution of the linearized Euler equations for aeroacoustic applications. For large-eddy simulation, the...

An overview of numerical methods for acoustic wave propagation

This paper presents a short overview of recent developments of low-dispersive and low-dissipation finite-difference schemes as an alternative to more classical methods of applied mathematics. Needs of accurate and efficient numerical solvers in computational aeroacoustics have motivated these developements over the last two decades. Properties...

Noise Sources in Single and Coaxial Jets

The acoustic simulations of a cold single stream jet at Mach number 0.9 and Reynolds number 3,600 and two heated coaxial jets at Mach number 0.9 and Reynolds numbers 3,600 and 400,000 are performed. The computation of the acoustic field is performed by a two-step approach using a large-eddy simulation (LES) for the flow field and approximate...

Design Exploration of Shielding Effect for Aircraft Engine Noise

The multi-objective design exploration of the two-dimensional shielding effect for engine noise using V-tale wing has been performed. Two objective functions are considered as the minimization of the sound pressure level at the side and bottom locations relative to the fuselage, which values are evaluated by using the linearized Euler equation....

Computation of Modal Radiation through an Engine Exhaust on Adaptively Refined Meshes

This paper outlines the method of a block-structured adaptive mesh refinement (AMR) and its application to the computation of noise radiation from a realistic engine exhaust geometry with flow. The computational model described allows acoustic waves, propagating inside the bypass duct of a generic aircraft engine, to be admitted into a...