Computational Aeroacoustics Analysis of Aircraft Engines

Objective: Computation of sound fields radiated from turbofan engines.

Methodology: As we are interested in only sound propagation, we solve numerically the Euler (inviscid fluid) equations. The source of sound is considered given in terms of spinning modes. Two codes have been developed, one in the frequency domain and the other one in the time domain. Both codes use a spectral element formulation (although the first is a classical one with continuous basis functions, and the latter a Discontinuous Galerkin formulation).

Computed SPL (Sound Pressure Level) contours for a small business jet aircraft.

A snapshot of the acoustic pressure contours for the same aircraft, at the first BPF (Blade Passing Frequency).