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Conceptual design and numerical studies of active flow control aerofoil based on shape-memory alloy and macro fibre composites

Part of: International Symposium on Smart Aircraft 2019

Published online by Cambridge University Press:  04 March 2021

W. Zhang Open the ORCID record for W. Zhang [Opens in a new window] ,
X.T. Nie ,
X.Y. Gao  and
W.H. Chen
W. Zhang
Affiliation:
College of Aerospace Science and Engineering National University of Defense TechnologyChangshaChina and China Aerodynamics Research and Development CenterMianyangChina
X.T. Nie
Affiliation:
China Aerodynamics Research and Development CenterMianyangChina
X.Y. Gao
Affiliation:
China Aerodynamics Research and Development CenterMianyangChina
W.H. Chen*
Affiliation:
China Aerodynamics Research and Development CenterMianyangChina
*
chenwanhua@cardc.cn
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Abstract

Active flow control for aerofoils has been proven to be an effective way to improve the aerodynamic performance of aircraft. A conceptual hybrid design with surfaces embedded with Shape-Memory Alloy (SMA) and trailing Macro Fibre Composites (MFC) is proposed to implement active flow control for aerofoils. A Computational Fluid Dynamics (CFD) model has been built to explore the feasibility and potential performance of the proposed conceptual hybrid design. Accordingly, numerical analysis is carried out to investigate the unsteady flow characteristics by dynamic morphing rather than using classical static simulations and complicated coupling. The results show that camber growth by SMA action could cause an evident rise of Cl and Cd in the take-off/landing phases when the Angle-of-Attack (AoA) is less than 10°. The transient tail vibration behaviour in the cruise period when using MFC actuators is studied over wide ranges of frequency, AoA and vibration amplitude. The buffet frequency is locked in by the vibration frequency, and a decrease of 1.66–2.32% in Cd can be achieved by using a proper vibration frequency and amplitude.

Keywords

AerodynamicsActive flow controlSMA: MFCRAE 2822
Type
Research Article
Information
The Aeronautical Journal , Volume 125 , Issue 1287 , May 2021 , pp. 830 - 846
Copyright
© The Author(s), 2021. Published by Cambridge University Press on behalf of Royal Aeronautical Society

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