Response of a Panel to Shock Impingement: Modeling and Comparison with Experiments

Abstract

A preliminary assessment is developed for long time record modeling and simulation of coupled flow-structural response of thin-gauge panels subject to shock impingements. The study is based on a set of recent discovery experiments carried out by the Air Force Research Laboratory. The fluid loads are modeled using a CFD surrogate for the steady surface pressure combined with engineering level approximations for unsteady pressure fluctuations due to panel vibration and boundary layer turbulence. The structure is modeled using both full-order and reduced-order finite element formulations. Initial comparisons indicate reasonable confidence in modeling the steady component of pressure and structural modeling, and less confidence in modeling the fluctuating pressure and dynamic panel response. Several sources of modeling and measurement uncertainties are highlighted.

Experiments on Aerothermal Supersonic Fluid-Structure Interaction

“…Panel response was drastically changed in comparison to the no-shock case and, depending on the shock position, the maximum amplitude of the panel deformation was significantly increased. Numerical results by [21,22] suggest that while good agreement on mean quantities was achieved it is crucial for the prediction of the dynamics of the coupled system to take into account the intrinsic unsteadiness of SWBLI. FSI experiments with SWBLI with a different focus were conducted by [5,6].…”