Identification of the aeroacoustic response of a low Machnumber flow through a T joint

摘要

A methodology to study numerically the aeroacoustic response of low Mach number confined flowsto acoustic excitations is presented. The approach combines incompressible flow computations,vortex sound theory, and system identification techniques, and is applied here to study the behaviorof a two-dimensional laminar flow through a T joint. Comparison with experimental resultsavailable in literature shows that the computed source models capture the main physicalmechanisms of the sound production in the shear layer of the T joint.