Exploration of Nozzle Flow Circumferential Attenuation and Efficient Expansion for Rotating Detonation Rocket Engines

摘要

Previous works have shown that the time averaged azimuthal velocity component exhibit overall low velocity magnitudes. On an instantaneous basis however, mitigation of local swirl in the exhaust of rotating detonation engines has proven necessary, which has made engine integration and optimum power extraction from the engine more difficult. The work in this paper outlines the design process for several novel back-end nozzle configurations for a rocket rotating detonation engine to dampen the fluctuating azimuthal velocity component. Velocimetry measurements are conducted in the exhaust plume of the RDE to assess nozzle influence on flow straightening.