Numerical Investigation of a Slender Delta Wing with Antisymmetric Leading-Edge Flap Deflection
Publication: Journal of Aerospace Engineering
Volume 36, Issue 1
Abstract
The leading-edge flap (LEF) on a delta wing is an attractive tool because it can regulate the vortex strength and structure by changing the separation position along the leading edge. This paper aims to evaluate the control effectiveness of the LEF through numerical approaches. A moving mesh technique, which is developed based on the radial basis function method, is adopted to simulate the deflection process of the LEF. Static and dynamic deflections are studied numerically to explore their effects on the aerodynamic performance and the vortical structure of the delta wing. The results show that the asymmetric deflection of the LEF leads to an asymmetric distribution of the leeward vortices, which generates nonzero lateral forces and moments varying linearly with the deflection angle. During the dynamic deflection process, the flap deflecting downward fed more vorticity to the primary vortex on the same side, and vice versa. The amplitude of the lateral force and moment changes linearly with the deflection angle by which their frequencies are determined.
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Data Availability Statement
Some or all data, models, and code that support the findings of this study are available from the corresponding author upon reasonable request.
Acknowledgments
This work was supported by the Chinese National Key Project (No. GJXM92579).
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Published In
Journal of Aerospace Engineering
Volume 36 • Issue 1 • January 2023
Copyright
© 2022 American Society of Civil Engineers.
History
Received: Dec 19, 2021
Accepted: Jun 7, 2022
Published online: Oct 31, 2022
Published in print: Jan 1, 2023
Discussion open until: Mar 31, 2023
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