An Experimental Investigation Into Shock-Induced Panel Flutter

Study into the effect of mean surface deformation and wind tunnel boundary conditions on panel flutter

Master thesis (2024)

Authors

M. Radaelli Aerospace Engineering

Contributors

F.F.J. Schrijer Aerodynamics - Aerospace Engineering (mentor)
B.W. van Oudheusden Aerodynamics - Aerospace Engineering (mentor)
A. D'Aguanno Aerodynamics - Aerospace Engineering (mentor)
J. Sodja Group Sodja - Aerospace Engineering (graduation committee member)
S.J. Hulshoff Aerodynamics - Aerospace Engineering (graduation committee member)
Faculty
Aerospace Engineering
More Info
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Published Date

16-09-2024

Language

English

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Faculty

Aerospace Engineering

Abstract

The aerospace industry’s push for faster, lighter, and more durable designs highlights the critical challenge of panel flutter in supersonic flight, a poorly understood phenomenon intensified by shock-wave/boundary-layer interactions (SWBLI). This study experimentally investigates the effects of static and dynamic panel deformations on shock-induced panel flutter at Mach 2.0, using open, closed, and ventilated cavity conditions. Results show that cavity closure significantly influences panel response, with the open cavity causing greater oscillations due to strong pressure waves entering it, causing resonance behaviour; closing the cavity seems to filter out this resonance behaviour. Additionally, temperature changes and wind tunnel confinement were identified as factors affecting panel and flow behaviour. The results underscore the importance of understanding experimental conditions to accurately interpret fluid-structure interactions in supersonic conditions.