Aircraft airframe noise: Slat noise attenuation with acoustic liner treatment
Last updated on April 5, 2022
The significant contribution of the flows around the leading edge slat on the wing of a commercial aircraft to the airframe noise during approach and landing motivates this research project to identify the mechanisms of leading edge slat noise and passively control these acoustic sources. Several flow phenomena take place due to the separated flow in the slat cove region and its interaction with the surrounding flow such as, low-speed recirculation flow, free shear layer, and ejections of large-scale structures merging with the slat wake. Other important phenomena can also exist, such as, the interaction of the slat wake with the wing boundary layer, referred to as the confluent boundary layer, and slat trailing edge vortex shedding. All of these may cause the noise generation. To understand the physics and mechanisms behind these phenomena and to find a way to reduce the slat noise, accurate simulations of the complex unsteadiness flow of the high-lift wing are needed. To develop and apply computational aeroacoustic methods using the SotonCAA code to reveal the mechanism of the slat noise generation and demonstrate the feasibility of controlling the slat noise using acoustic liners.
