Exploring the Effect of Different Shock Impingement Angles on Aeroelastic Response for a Thin Panel ifasd2024 Tracking Number 16Presentation: Session: Shocks Room: Room 1.3 Session start: 11:00 Tue 18 Jun 2024 Luisa Piccolo Serafim luisa.piccolo.serafim@duke.edu Affifliation: Duke University Earl Dowell earl.dowell@duke.edu Affifliation: Duke University Topics: - Computational Aeroelasticity (High and low fidelity (un)coupled analysis methods:), - Reduced Order Modeling (High and low fidelity (un)coupled analysis methods:), - High Speed Structural Dynamics Phenomena (High and low fidelity (un)coupled analysis methods:) Abstract: 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. |