Controlling a complex multi-stream supersonic jet flow

What is it about?

Simulations were performed for a complex multi-stream supersonic jet flow with active flow control. The nozzle of interests contains a core flow of Mach 1.6, and a bypass stream of Mach 1.0. The interaction between the two flows prior to the nozzle exit generates vortices that have been found to be the source of a resonant tone that dominates the flow field and far field acoustics. The goal of introducing control is to reducing noise, shock wave structures, and the intense surface loading experienced by the aircraft structure. Micro-jet actuators were placed at various spatial locations and the angle of actuation was parametrically tested.

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Photo by Hermeus on Unsplash

Photo by Hermeus on Unsplash

Why is it important?

The multi-stream supersonic engine provides various advantages in terms of lift augmentation, drag reduction, and overall engine thermal management. However, the engine exit still possess various undesired features. Understanding and successfully controlling the aerodynamic flow at the nozzle exit will further optimize and improve upon this design such that next generation military jets can achieve a higher performance.