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Title: Dynamic Mode Decomposition Study of a RDRE Exhaust for Swirl Attenuation Using Various Nozzle Configurations
The attenuation of circumferential flow inherent in Rotating Detonation Rocket Engines (RDRE) through nozzle configurations is studied. The method used in this investigation consist of capturing highspeed side images of the exhaust to visualize the swirling flow. The images were processed through a dynamic mode decomposition code to resolve the main frequencies of the flow field at the exhaust. The obtained results were compared to the operational frequency of the engine computed with back-end images. Nozzle configurations were shown to have an influence on wave dynamics due to the induced back pressure. Results from the DMD method show similarity to those obtained from detonation surfaces. The nozzle configurations investigated are: 1) baseline without a nozzle, 2) aerospike nozzle only without the outer nozzle and 3) the inner and outer nozzles in conjunction.  more » « less
Award ID(s):
1852130
PAR ID:
10389403
Author(s) / Creator(s):
; ; ; ; ;
Date Published:
Journal Name:
AIAA SciTech 2022 Forum
Format(s):
Medium: X
Sponsoring Org:
National Science Foundation
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