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Proposing Institution

Lehrstuhl für Aerodynamik, TU München
Project Manager

Vito Pasquariello
Boltzmannstr. 15
85748 Garching
In the context of launch vehicles, shock-wave/boundary-layer interactions (SWBLI) are common flow features that may generate high-magnitude transient side loads. The interaction can critically affect the rocket nozzle performance in case of shock-induced boundary-layer separation and it is a main source of maximum mean and fluctuating pressure loads that the underlying structure is exposed to. With future rocket technologies focusing on optimal weight systems, fluid-structure interactions (FSI) become significant and must be taken into account in the design process in order to ensure the structural integrity. Multi-disciplinary numerical tools are necessary for a correct prediction of the complex flow physics influenced by structural deformations.Within the collaborative research program "Transregio 40" one objective is to develop high-fidelity numerical tools for an integrated interdisciplinary design process. For our studies we developed a Finite Volume - Finite Element coupling approach for the solution of compressible FSI problems based on a staggered Dirichlet-Neumann partitioning, where the interface motion within the Eulerian flow solver is accounted for by means of a cut-element based immersed boundary method. Coupling conditions at the non-matching conjoined interface are enforced using a Mortar method.In this study we will perform high-fidelity large-eddy simulations (LES) of FSI problems in the context of overexpanded rocket nozzles with a focus on the aeroelastic interaction of the massively separated flow-region with structural modes. To the authors knowledge, this is the first time a wall-resolved LES of a turbulent SWBLI is coupled to a structural solver. Besides mean and instantaneous flow quantities, we investigate unsteady aspects by means of wall-pressure spectra and the influence of the panel motion on turbulence.

Impressum, Conny Wendler