Please use this identifier to cite or link to this item: http://hdl.handle.net/2440/112581
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Type: Theses
Title: Numerical study of wall-mounted finite span wings
Author: Coombs, Jesse Lee
Issue Date: 2017
School/Discipline: School of Mechanical Engineering
Abstract: The extensive use of hydrofoils and airfoils in applications including domestic and military, air, water, and land vehicles, as well as air-conditioning and wind turbines, means that their design for minimally noisy and maximum aerodynamic performance, is not only an important issue for defence, but one with broader economic, health and environmental ramifications. Wall-mounted finite span wing flows occur when a boundary layer developing on a surface encounters a hydrofoil or airfoil attached to that surface. Although fundamental to various engineering fields, there is a lack of insight into the underlying physics of these flows. Particularly important is the noise created by the complex flow structures associated with them. The main objective of this work is to investigate the noise and associated flow structures of wall-mounted finite span wings and to develop noise prediction methods for these flows. A number of recent wall-mounted finite span wing experiments (Moreau et al., 2015; Moreau and Doolan, 2013) involving flat ended finite length wings attached to flat plates are simulated using three-dimensional Reynolds Averaged Navier Stokes (RANS) based methods, which provide greater insight into the complete flow structure than is available from the original experiments. The flow structures are observed and compared with experimental measurements. A flow topology model is developed to describe the observed tip vortex formation process for the zero angle of attack condition. Existing leading and trailing edge noise models that are suitable for predicting the noise from 2D airfoils are extended to be applicable for 3D airfoil applications, allowing spanwise variations in geometric and flow properties to be taken into account. Additionally, an isolated tip noise model is developed based on the size of the tip vortex obtained from RANS flow simulations. The developed noise models have been validated against experimental measurements and have been shown to agree well and thus provide a means for prediction of the noise produced by wall-mounted finite span wing flows. The increased understanding of the wall-mounted finite span wing flow structures and the increased capacity of the developed wall-mounted finite span wing flow noise modelling is expected to have applications in the design of airfoils and hydrofoils with improved aerodynamic and aeroacoustic performance.
Advisor: Zander, Anthony Charles
Doolan, Cornelius Joseph
Moreau, Danielle J.
Brooks, Laura Anne
Dissertation Note: Thesis (Ph.D.) -- University of Adelaide, School of Mechanical Engineering, 2017
Keywords: wall mounted finite span wing
wing noise model
trailing edge noise
tip noise
Provenance: This electronic version is made publicly available by the University of Adelaide in accordance with its open access policy for student theses. Copyright in this thesis remains with the author. This thesis may incorporate third party material which has been used by the author pursuant to Fair Dealing exceptions. If you are the owner of any included third party copyright material you wish to be removed from this electronic version, please complete the take down form located at: http://www.adelaide.edu.au/legals
DOI: 10.4225/55/5b109447b84c0
Appears in Collections:Research Theses

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