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Flow Around a Leading-Edge Slat: Part I — Turbulent Flow Statistics

[+] Author Affiliations
Patrick R. Richard, Stephen J. Wilkins, Joseph W. Hall

University of New Brunswick, Fredericton, NB, Canada

Paper No. PVP2014-28316, pp. V004T04A002; 7 pages
doi:10.1115/PVP2014-28316
From:
  • ASME 2014 Pressure Vessels and Piping Conference
  • Volume 4: Fluid-Structure Interaction
  • Anaheim, California, USA, July 20–24, 2014
  • Conference Sponsors: Pressure Vessels and Piping Division
  • ISBN: 978-0-7918-4601-8
  • Copyright © 2014 by ASME

abstract

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.

Copyright © 2014 by ASME

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