Flow and acoustics in a model rocket flame deflector and deflector cover

The design of a rocket launch environment is complex process with many different aspects that are highly interconnected. Acoustics, which one these, should be investigated in detail due to possible devastating effects on the vehicle, crew, and environment. This study uses numerical method consider passive noise reduction applied supersonic jet impinging an inclined flame deflector decrease acoustic loads vehicle levels far-field. In flat plate configuration, waves travel upstream originate from impingement wall regions. These traveling combination produced by high speed flows region reflect wall. Due inclination plate, these either far-field direction or towards free-jet interacting flow near nozzle lip. interaction can create self sustaining feedback loop, cause tones appear near- spectra. It aim present block introducing second circular cut-out between exit plate. Different configurations locations sizes using Detached Eddy Simulation CFD solver based Ffowcs Williams Hawkings analogy. mechanisms for establishment loops examined.