5 August 2024
The paper was called “Swirling flow effects on highly-heated aerospike nozzle jets”. It deals with the characterization of the flow characteristics and the resulting aeroacoustic features of a supersonic aerospike nozzle subject to high temperature boundary conditions (up to 2000K) with a swirling component. It is a preliminary study to understand how a single swirl number affects the supersonic jet and is relevant to later grasp how rotating detonation combustion will influence the jet and the corresponding aeroacoustic signature. We found that swirling flow leads to weaker Mach wave radiation and lower Overall Sound Pressure Levels compared to the baseline cases without swirl. https://www.aiaa.org/events-learning/event/2024/06/04/default-calendar/30th-aiaa-ceas-aeroacoustics-conference