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  1. Free, publicly-accessible full text available August 4, 2024
  2. The Rotating Detonation Engine has been seen as the next step for rocket propulsion applications with the advent of the Rotating Detonation Rocket Engine, an engine configuration developed by the Air Force Research Laboratory. In an effort to flight-test this engine and provide a dataset to train detonation-based simulation, the Rotating Detonation Rocket Engine has been tested in a collaborative effort including the University of Central Florida. For this testing, a thrust stand was developed to obtain the key thrust and impulse data necessary for advancing the engine to flight readiness. This thrust stand utilized the small-scale of the Rotating Detonation Rocket Engine to motivate an axial-loading measurement approach and the integration of an automatic-calibration subassembly, altogether which allows for incredibly accurate thrust measurements from an engine. Results using this thrust stand for two similar engine configurations are shown to validate the operation of the thrust stand. 
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  3. 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. 
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