Abstract
A general aeroacoustic boundary condition in the time domain for the broadband frequency noise is crucial for solving aeroacoustic problems. An impedance boundary condition implemented in the commercial code ANSYS Fluent 15.0 Navier-Stokes solver allows specifying the aero-acoustic behavior at flow boundaries and soft walls. The input format is a reflection coefficient derived from specific impedance and is in the form of a complex polynomial function of frequency. This newly-implemented boundary condition in Fluent allows improved solutions of industrial applications in aeroacoustics where partial reflection is important. The liner impedance in turbo-machinery and mufflers is one of the applications. The present paper will discuss the numerical implementation of an impedance flow BC in Fluent and demonstrate the applicability of this boundary condition on two test cases. In the first test case, a comparison is carried out with a two parameters model for the real pole and the complex pole. For the second test case, a two dimensional CAA analysis is carried out for a NASA impedance flow Tube (GIT) and validated with experimental results.
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