Static and Forced Motion Aeroelastic Simulations of the HIRENASD Wind Tunnel Model

Abstract

The article presents steady and unsteady aeroelastic simulation results for selected test cases of the HIRENASD wind tunnel configuration. The consideration of the static elastic deformation of the wing proved to be indispensable for the steady simulations. Therefore, static coupling simulations have been conducted where the structural deformation of the wing was calculated with a modal approach. The unsteady simulations were simplified in such a way that the elastic motion of the wing in a certain structural eigenmode was prescribed in a forced motion CFD simulation using mesh deformation. Yet this approach yields satisfying results in terms of the unsteady pressure distribution. Furthermore, two finite element models comprising different levels of detail are compared in the forced motion simulations. Any CFD simulations have been conducted with the DLR TAU code, an unstructured, node-centered flow solver based on finite volume discretization in ALE formulation. Simulation results are presented together with the corresponding experimental data.