Abstract

A novel airfoil noise reduction technique, based on morphing structures, has been introduced and investigated. In order to achieve high aerodynamic performance and reduce the noise, a new morphing flap concept based on a bending stiffness tailored honeycomb core with zero Poisson's ratio has been developed. The response of the morphing structure to an internal actuation force is investigated using a two-dimensional finite element model. In this study, a NACA 63-418 airfoil of chord 1.3m has been fitted with the morphing flap. The aerodynamic and acoustic performance of the airfoil is studied using Xfoil and the BPM semi-empirical airfoil noise prediction model. A parametric study is provided for the effects of the changes to the profile and curvature of the pressure and suction sides of the airfoil trailing edge. The effectiveness of the proposed method is investigated at different Mach numbers and angles of attack. Results have shown that both the aerodynamic and acoustic performance of the airfoil will significantly improve as a result of the morphing trailing edge. Also, the preliminary optimization of the morphing flap design has shown that by changing the bending stiffness of the honeycomb core along the chord, the morphing profile can be tailored, leading to aerodynamic performance improvement and significant noise reduction at low frequencies.

Original languageEnglish
Title of host publication21st International Congress on Sound and Vibration 2014, ICSV 2014
PublisherInternational Institute of Acoustics and Vibrations
Pages1840-1847
Number of pages8
ISBN (Electronic)9781634392389
Publication statusPublished - 1 Jan 2014
Event21st International Congress on Sound and Vibration 2014, ICSV 2014 - Beijing, China
Duration: 13 Jul 201417 Jul 2014

Publication series

Name21st International Congress on Sound and Vibration 2014, ICSV 2014
Volume2

Conference

Conference21st International Congress on Sound and Vibration 2014, ICSV 2014
CountryChina
CityBeijing
Period13/07/1417/07/14

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  • Cite this

    Ai, Q., Azarpeyvand, M., Lachenal, X., & Weaver, P. M. (2014). Airfoil noise reduction using morphing trailing edge. In 21st International Congress on Sound and Vibration 2014, ICSV 2014 (pp. 1840-1847). (21st International Congress on Sound and Vibration 2014, ICSV 2014; Vol. 2). International Institute of Acoustics and Vibrations.