On the Effect of Trailing-Edge Bluntness on Airfoil Noise

Authors

Keywords:

airfoil noise, trailing edge bluntness.

Abstract

 The purpose of this study is to experimentally investigate the effect of trailing edge bluntness on the generation of airfoil tonal noise at different angles of attack and low to moderate Reynolds numbers. Detailed aeroacoustic measurements are made for an airfoil at three angles of attack: 00, 50, and 100. Airfoil chord-based Reynolds numbers analyzed are 2.8 ×105, 3.7 ×105 and 5 ×105, corresponding to free stream velocities of 14, 18 and 24 m/s, respectively. The airfoil noise with a straight trailing edge is seen to change from a broadband hump to intensive tonal noise with increasing angle of attack, while it changes from tonal noise to a broadband hump with increasing Reynolds number. Moreover, results show that for higher values of Reynolds numbers the dominant tonal peak decreases in amplitude and shifts to higher frequencies. In general, it is observed that as the trailing edge bluntness increases, the dominant tonal peaks have larger overall amplitudes. 

Author Biography

Joana Rocha, Carleton University

Dr. Joana Rocha is an Associate Professor and Associate Chair in the Department of Mechanical and Aerospace Engineering at Carleton University, in Ottawa. Before joining Carleton University, Dr. Rocha was a Visiting Researcher at NASA Langley Research Centre and the National Institute of Aerospace, in Virginia, USA. She received her Ph.D. and M.A.Sc. degrees at the University of Victoria, in Victoria, where her research focused on the development of models for the prediction of flow-induced noise in aircraft. Since joining Carleton University as a Professor in 2012, Dr. Rocha has established the Aeroacoustics Research Laboratory, with unique capabilities. The aeroacoustic high-speed wind tunnel allows Dr. Rocha and her team to develop state-of-the-art research in areas such as aircraft noise prediction and reduction. Dr. Rocha’s research focuses on aircraft noise prediction, design and optimization of aircraft structures for noise reduction, aeroacoustics, turbulent-flow induced noise, structural-acoustics, and turbulence modelling with applications in aerospace. Through her research, Dr. Rocha aims to design and develop new aircraft concepts that are quieter.

Additional Files

Published

2022-07-25

How to Cite

1.
Al Tlua B, Rocha J. On the Effect of Trailing-Edge Bluntness on Airfoil Noise. Canadian Acoustics [Internet]. 2022 Jul. 25 [cited 2024 Nov. 21];50(1). Available from: https://jcaa.caa-aca.ca/index.php/jcaa/article/view/3476

Issue

Vol. 50 No. 1 (2022)

Section

Article - Aeroacoustics

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