Local Aeroelastic Instability of High-Speed Cylindrical Vehicles

What is it about?

A pressurized circular cylindrical shell structure's aeroelastic stability when exposed to supersonic flow is analyzed via finite element analysis and a reduced order modal analysis. The resulting aeroelastic stability boundaries are compared to previously published theoretical, numerical, and experimental results. Also, for the first time, the aeroelastic stability of such a shell structure when inclined to the flow is investigated and used to inform future studies where maneuvering high-speed vehicles will be required to take on aggressive angles of attack.

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