Dedicated numerical simulations of vortex-nozzle interaction indirect noise in solid rocket motors (SRMs) are presented. It is assumed that the flow in the nozzle and hence the sound radiation is not significantly influenced by the global acoustic oscillation of a SRM. Therefore, the study is limited to the acoustic response of a semi-infinite pipe terminated by a choked nozzle. The nozzle considered here is placed flush in a wall forming a right angle to the walls of the combustion chamber. The study focuses on where sound is produced due to vortex-nozzle interaction. The presented results indicate that sound is produced when the vortex is on its approach to the nozzle, rather than by impingement of the vortex on the nozzle walls.

Original languageEnglish
Title of host publication25th AIAA/CEAS Aeroacoustics Conference
Subtitle of host publication20-23 May 2019 Delft, The Netherlands
Number of pages14
ISBN (Electronic)978-1-62410-588-3
Publication statusPublished - 2019
Event25th AIAA/CEAS Aeroacoustics Conference - Delft, Netherlands
Duration: 20 May 201923 May 2019
Conference number: 25


Conference25th AIAA/CEAS Aeroacoustics Conference
Internet address

ID: 55248523