High Performance Computing Towards Silent Flows

Wolfgang Schröder

Institute of Aerodynamics, RWTH Aachen University
Wüllnerstr. zw. 5 und 7, 52062 Aachen, Germany

The flow field and the acoustic field of various jet geometries and a high-lift configuration consisting of a deployed slat and a main wing are numerically analyzed. The flow data, which are computed via large-eddy simulations, provide the distributions being plugged in the source terms of the acoustic perturbation equations or the Ffowcs-Williams and Hawkings equation to compute the acoustic near field. The investigation emphasizes the core flow to have a major impact on the radiated jet noise. Furthermore, the analysis shows the interaction of the shear layer of the slat trailing edge and the slat gap flow to generate higher vorticity than the main airfoil trailing edge shear layer. Thus, the slat gap is the more dominant noise region for an airport approaching aircraft.

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