This work is focused on a hypersonic aeroelastic experiment involving a shock impinging on
compliant cantilevered plate at Mach 5.8. The shock induces a pressure differential across …

Global surface pressure measurements have been carried out on a 7° half-angle circular
cone/flare model at nominally zero angle of attack using pressure-sensitive paint (PSP) …

The flow structure coupling generated by an impinging shock boundary layer interactions
(SBLI) flowfield over a rectangular panel is investigated. The impinging oblique shock is …

This paper reports experimental results of fluid/structure interactions induced by shock
impingement on a clamped-free/clamped-free compliant panel in a Mach 5.8 Ludwieg tube …

This work discusses the design, measurement, and simulation of an oscillating shock-
wave/boundary-layer interaction on a flat plate at Mach 5.8 and R e∞= 7× 10 6 m− 1. The …

The response and performance of an aeroelastic hypersonic intake was studied
experimentally using fundamental geometry and structural boundary conditions. The …

View Video Presentation: https://doi. org/10.2514/6.2021-2926. vid Following the
investigations into the FSI of a thin compliant plate in supersonic flows in our earlier efforts …

View Video Presentation: https://doi. org/10.2514/6.2023-4134. vid Experiments on a rigid
panel were conducted to characterize the mean and unsteady pressure fields beneath a …

View Video Presentation: https://doi. org/10.2514/6.2023-1178. vid Surface pressure
distributions of a hypersonic shock-wave/boundary-layer interaction have been investigated …

The global surface pressure was measured on a 7° half-angle circular cone/flare model at a
nominally zero angle of attack using pressure-sensitive paint (PSP). These experiments …