As aircraft engine noise continues to decrease with advancing research, the focus has been partially shifted to airframe noise. One of the main sources of airframe noise are high lift devices, which includes the leading-edge slat on wings. The leading-edge slat works along with the tail flap to provide increased lift to the aircraft during takeoff and landing. This paper will present the findings of an experimental investigation aimed at identifying the sources of noise produced by the leading-edge slat geometry. The main focus of the experiments was the slat cove. Small scale wind tunnel experiments were undertaken at the University of New Brunswick using Particle Image Velocimetry (PIV) to obtain time-averaged Turbulent Kinetic Energy (TKE), Reynolds stresses and vorticity. The experiments were performed at Reynolds numbers of 156,000 and 312,000 for an angle of attack of 20 degrees. The results indicate the presence of a strong shear-layer formed at the slat cusp which is likely to be an significant source of aeroacoustic noise.
Flow Around a Leading-Edge Slat: Part I — Turbulent Flow Statistics
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Richard, PR, Wilkins, SJ, & Hall, JW. "Flow Around a Leading-Edge Slat: Part I — Turbulent Flow Statistics." Proceedings of the ASME 2014 Pressure Vessels and Piping Conference. Volume 4: Fluid-Structure Interaction. Anaheim, California, USA. July 20–24, 2014. V004T04A002. ASME. https://doi.org/10.1115/PVP2014-28316
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