Numerical aeroelastic investigations are conducted for the Model53 delta wing with a deployed slat and two trailing-edge control surfaces at transonic speed and high dynamic pressure. The numerical method is based on coupled high-fidelity CFD-CSM simulations, which is implemented in the multi-disciplinary simulation environment SimServer. The DLR Tau Code is utilized to solve the Reynolds-Averaged Navier-Stokes (RANS) equations and a modal solver is employed to calculate the structural displacem... »
Aeroelasticity; Chimera; Control surfaces; Delta wing
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Notes on Numerical Fluid Mechanics and Multidisciplinary Design
The fruitful collaboration with Airbus Defence and Space and its partial financial research support is gratefully acknowledged. The authors also thank the Gauss Centre for Supercomputing e.V. (www.gauss-centre.eu) for supporting this project by providing computing time on the GCS Supercomputer SuperMUC-NG at Leibniz Supercomputing Centre (www.lrz.de).