The use of a fairing and split plate for bluff body noise control


Spiteri, M., Zhang, X., Molin, N. and Chow, L. (2008) The use of a fairing and split plate for bluff body noise control. In, 14th AIAA/CEAS Aeroacoustics Conference, Vancouver, Canada, 05 - 07 May 2008. Reston, US, American Institute of Aeronautics and Astronautics12pp.

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Description/Abstract

Landing gears have been identified as major noise source contributors during the aircraft’s approach to landing phase. Techniques such as using fairings to alter the flow around the landing gear components have shown to reduce noise1 . This study investigates methods to further improve the fairing performance. A fundamental study has been performed to understand the influence of using a fairing on a simple cylindrical strut when a split plate is placed in the cavity between the fairing and the strut. Aerodynamic and acoustic tests are performed. Windtunnel tests equipped with a phased microphone array as well as far field measurements have been conducted out on the fairing-cylindrical strut configuration. The results show that the splitter plate either reduces or eliminates the vortex shedding which in turn reduces noise. This is due to the dividing plate blocking the interaction between the two opposing shear layers aft of the fairing’s trailing edge and reducing their interaction with the downstream strut. Lower velocities around the shell and the strut are observed with the use of the splitter plate as well as reduction of recirculating flow within the shell strut cavity. This alteration in the flow characteristics results in a broadband noise reduction and hence reducing the self-noise generated by the fairing.

Item Type: Conference or Workshop Item (Paper)
Related URLs:
Subjects: T Technology > TL Motor vehicles. Aeronautics. Astronautics
Divisions: University Structure - Pre August 2011 > School of Engineering Sciences > Aerodynamics & Flight Mechanics
ePrint ID: 64085
Date Deposited: 01 Dec 2008
Last Modified: 27 Mar 2014 18:45
Publisher: American Institute of Aeronautics and Astronautics
URI: http://eprints.soton.ac.uk/id/eprint/64085

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