TY - GEN
T1 - Leveraging surface aeroacoustic-structural interaction for airfoil tonal noise reduction
AU - Arif, Irsalan
AU - Lam, Garret C.Y.
AU - Leung, Randolph C.K.
AU - Wu, Di
N1 - Funding Information:
The authors gratefully acknowledge the support given by the Central Research Grant of the Hong Kong Polytechnic University under grant G-YBGF. The third author acknowledges the support with a research donation from the Philip K. H. Wong Foundation under grant 5-ZH1X. The first and last authors acknowledge the support with research studentship tenable at Department of Mechanical Engineering, The Hong Kong Polytechnic University.
Publisher Copyright:
© 2019, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
Copyright:
Copyright 2020 Elsevier B.V., All rights reserved.
PY - 2019
Y1 - 2019
N2 - In this paper, a passive method of airfoil tonal noise control is investigated by using an elastic panel flush mounted on the suction surface of a NACA 0012 airfoil at an angle of attack of 50 and flow velocity of Mach number 0.4. Direct Aeroacoustics Simulation along with Linear Stability Analysis is used to study the interaction between airflow and elastic panel mounted on suction surface of airfoil. Panel parameters are carefully selected to ensure that the natural frequency of panel in the presence of flow field is similar to that of flow frequency. A parametric study is carried out based on different panel parameters including material density, panel thickness and internal tension to analyze the sensitivity of parameters on panel response to instability wave over the airfoil, subsequently modifying panel vibration behavior and reducing the tonal noise. Six different cases are analyzed and their performance is evaluated in terms of tonal noise reduction. Numerical results indicate a significant improvement in noise reduction is achieved for all cases as compared to previous study. Contribution of panel density and thickness in noise reduction are found to be dominant based on comparative study.
AB - In this paper, a passive method of airfoil tonal noise control is investigated by using an elastic panel flush mounted on the suction surface of a NACA 0012 airfoil at an angle of attack of 50 and flow velocity of Mach number 0.4. Direct Aeroacoustics Simulation along with Linear Stability Analysis is used to study the interaction between airflow and elastic panel mounted on suction surface of airfoil. Panel parameters are carefully selected to ensure that the natural frequency of panel in the presence of flow field is similar to that of flow frequency. A parametric study is carried out based on different panel parameters including material density, panel thickness and internal tension to analyze the sensitivity of parameters on panel response to instability wave over the airfoil, subsequently modifying panel vibration behavior and reducing the tonal noise. Six different cases are analyzed and their performance is evaluated in terms of tonal noise reduction. Numerical results indicate a significant improvement in noise reduction is achieved for all cases as compared to previous study. Contribution of panel density and thickness in noise reduction are found to be dominant based on comparative study.
UR - http://www.scopus.com/inward/record.url?scp=85095964391&partnerID=8YFLogxK
U2 - 10.2514/6.2019-2758
DO - 10.2514/6.2019-2758
M3 - Conference article published in proceeding or book
AN - SCOPUS:85095964391
SN - 9781624105883
T3 - 25th AIAA/CEAS Aeroacoustics Conference, 2019
BT - 25th AIAA/CEAS Aeroacoustics Conference, 2019
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - 25th AIAA/CEAS Aeroacoustics Conference, 2019
Y2 - 20 May 2019 through 23 May 2019
ER -