Abstract
This paper is concerned with a mathematical model of a simple axisymmetric silencer model consisting of an expansion chamber followed by a tailpipe. The unstable shear layer is modeled via a discrete vortex approach, based on axisymmetric vortex rings. The aeroacoustic model, which is described in the present short paper, is based on the Powell-Howe theory of vortex sound. The boundary integrals, which represent the scattering by the cavity and the tailpipe, are discretized via the boundary element method.
