Wake Modification and Noise Emission of Serrated NACA 65(12)-10 at Moderate Reynolds Number
Publication: Journal of Aerospace Engineering
Volume 34, Issue 5
Abstract
Large eddy simulation (LES) with Ffowcs Williams and Hawkings (FW-H) analogy is performed to investigate the flow structure and noise emission of NACA 65(12)-10 aerofoil with and without a serrated trailing-edge at a moderate Reynolds number (). Following, the noise reduction mechanisms and the noise source regions are analyzed in detail. Results indicate that trailing-edge serrations reduce the overall sound pressure level by up to 6 dB at a 0° direction angle, and the noise reduction mainly occurs at a frequency lower than 10 kHz. The trailing-edge serrations can act as vortex generators and, thus, reorganize the vortex structure, altering the spanwise vortex to a large-scale streamwise vortex. Besides, serrations reduce the magnitude and modify the distribution of the power spectrum density of pressure fluctuation in the near wake, and the spanwise coherence magnitude is decreased. Additionally, the phase interference of acoustic sources at different spanwise positions is enhanced. Wavelet analysis reveals that the hump of the broadband noise spectrum of the serration aerofoil is mainly contributed by the serration tip region. The conclusion provides inspiration for further noise reduction by trailing-edge serrations.
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Data Availability Statement
All data, models, and code generated or used during the study appear in the published article.
Acknowledgments
This work was supported by the National Natural Science Foundation of China (11772146) and the Science, Technology, and Innovation Commission of Shenzhen Municipality (JCYJ20170817110605193).
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Published In
Journal of Aerospace Engineering
Volume 34 • Issue 5 • September 2021
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© 2021 American Society of Civil Engineers.
History
Received: Nov 17, 2020
Accepted: Mar 9, 2021
Published online: Jun 3, 2021
Published in print: Sep 1, 2021
Discussion open until: Nov 3, 2021
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