Direct numerical simulation of a supersonic jet and its acoustic field DEISA Extreme Computing Initiative

Shock-induced noise is generated by supersonic jets which are not perfectly expanded. This means that their nozzle exit pressure is above or below the ambient pressure. The flow adapts to the ambient pressure by a series of oblique shocks, compression and expansion waves. These interact with the shear layers, producing shock-induced or shock-associated noise. To this end direct numerical simulation will be performed to study the physical processes responsible, many of which have not yet been clearly identified. The main challenge is to simultaneously resolve the small-scale nonlinear turbulent structures and at the same time the large-scale, small amplitude acoustic waves they produce. Aims of this project In this project, the method of direct numerical sim-ulation will be used to compute a supersonic, three-dimensional and rectangular jet that is not perfectly expanded, as it is found at the nozzle exit of jet en-gines for aircraft. Numerical methods of high order of accuracy and possessing a suitable transfer functio