Flow Control Devices for Aeroacoustic Noise Suppression in Cavity Flow

Minimizing a radar cross-section during the design phase of advanced combat aircraft is crucial for enhancing battlefield survivability. Modern stealth aircraft, in contrast to traditional designs, use internal weapon bays, creating complex flow environments influenced by aeroacoustics, fluid–structure interaction, bay wall resonance, and pitch-up moments during ejection. This study employs numerical simulations using the M219 cavity model, integrating passive and active flow control devices to investigate aeroacoustic noise suppression and cavity flow control. The findings reveal that noise suppression is primarily achieved by displacing the shear layer away from the cavity opening, reducing energy transfer into the cavity, and mitigating vortex–pressure interactions. The passive leading-edge-inclined–trailing-edge-slanted integration model effectively suppresses Rossiter modes from [Formula: see text] to [Formula: see text] narrowband tones, while the active jet flow model achieves suppression at [Formula: see text] and [Formula: see text] but is less effective for broadband noise. Conversely, the negative leading-edge jet flow model shows limited noise suppression capabilities. These results provide critical insights into the effectiveness of diverse flow control strategies in managing cavity flow and aeroacoustic noise.