EXPLORING THE EFFECT OF DIFFERENT SHOCK IMPINGEMENT ANGLES ON AEROELASTIC RESPONSE FOR A THIN PANEL
In this study, a novel dynamically linearized Euler time-domain approach is used to compute the generalized aerodynamic force from a CFD simulation. The aerodynamic forcing term is implemented in a theoretical/computational nonlinear aeroelastic model to assess the dynamic response of a flexible clamped-clamped panel considering the pressure profile due to different shock wedge angles. One benefit of this approach is the possibility to perform the same analysis to solve the Navier-Stokes Equation via RANS simulation and consider the viscous boundary layer effect for near transonic regimes. Different shock wedge configurations will be explored in this study in the CFD/ROM simulation and the aeroelastic solution using an inviscid solver. These results will also be compared with the same structural configuration considering a modified Piston Theory model, exploring the limitations and opportunities of this simpler and faster solution.
