Numerical simulation of broadband shock-associated noise from a circular supersonic jet

The shock-associated noise from a supersonic jet is simulated with Large Eddy Simulation (LES) method. The full three dimensional filtered Navier-Stokes equations in cylindrical form are solved by a computational Aeroacoustics method. The Dispersion-Relation-Preserving scheme is used for spatial discretization and the low dissipation low dispersion Runge-Kutta method in 2N storage form is utilized for time marching. A 9-point high order explicit spatial filter is applied to replace the subgrid-scale (SGS) model. An adaptive artificial selective damping is used for shock capturing. The supersonic jets with Mach numbers 1.077, 1.166 and 1.221 are simulated. The instantaneous and time averaged flow field is analyzed. The far field noise spectra are obtained with Ffowcs Williams-Hawkings integration method and compared with the experimental data of Norum & Seiner. The Doppler shift of the predicted frequencies of the shock-associated noise peaks is observed. The predicted frequencies and amplitudes of the shock-associated noise peaks at most of angles agree fairly well with the experimental data of Norum & Seiner.