Large Eddy Simulation of Shock-Cell Noise From a Dual Stream Jet

This study will present the shock-cell noise results obtained from a large eddy aeroacoustic simulation from a dual stream jet. The primary stream is cold and subsonic with exit Mach number of M p = 0.89 and a Reynolds number of Re p = 0.57 × 10 6 . The secondary stream is cold supersonic and under-expanded with a perfectly expanded Mach number of Ms = 1.20 and Res = 1.66 × 10 6 . The computations are performed with the structured multi-block solver elsA. The aerodynamics and aeroacoustics of the flow are studied and analyzed in detail showing good agreement with experimental fits for the lengthscale and shear layer development, and capturing the broadband shock-cell noise in the near and far fields