TY - GEN
T1 - Flow-Induced Vibration Characteristics of a Fix-Supported Elastic Wing
AU - Peng, S.
AU - Tang, S. L.
AU - Alam, Md Mahbub
AU - Zhou, Yu
N1 - Publisher Copyright:
© 2021, The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd.
PY - 2021
Y1 - 2021
N2 - The aerodynamics and responses of an elastic high-aspect-ratio (AR = 9) NACA0012 airfoil with two-end-fixed supports were experimentally investigated. The chord-based Reynolds number is 1.5 × 105 and the angle of attack (α) of the wing varies from 0° to 90°. The lift, drag coefficients (Cl and Cd), deformation (A*, where the asterisk denotes normalization by the chord) of the wing, as well as the velocity fluctuation (u) in the wake were measured simultaneously. Based on the behaviors of Cl, Cd and A*, and their spectral coherences with u, four regimes are identified, i.e. α = 0º − 4º, 6º − 8º, 10º − 50º and 60º − 90º, respectively. In the regime of α = 0º − 4º, the wing keeps stable, while the dramatic structural vibration emerges for α in the range of 6º − 8º because of the occurrence of the flutter. As α is increased to stall angle (α = 10º), a rapid drop is observed in the RMS value of lift, drag and displacement. Beyond the stall angle, the fluctuation of lift and drag forces increases slowly with α in the range of 14º < α < 50º while the vibration of the displacement hardly changes. In this range, one pronounced peak corresponding to the vortex shedding occurs in their spectral coherences. As α overs 60º, the fluctuations in lift, drag and structural response are impaired, becoming negligibly small. The peak associated with vortex shedding in the spectral coherences is not distinct.
AB - The aerodynamics and responses of an elastic high-aspect-ratio (AR = 9) NACA0012 airfoil with two-end-fixed supports were experimentally investigated. The chord-based Reynolds number is 1.5 × 105 and the angle of attack (α) of the wing varies from 0° to 90°. The lift, drag coefficients (Cl and Cd), deformation (A*, where the asterisk denotes normalization by the chord) of the wing, as well as the velocity fluctuation (u) in the wake were measured simultaneously. Based on the behaviors of Cl, Cd and A*, and their spectral coherences with u, four regimes are identified, i.e. α = 0º − 4º, 6º − 8º, 10º − 50º and 60º − 90º, respectively. In the regime of α = 0º − 4º, the wing keeps stable, while the dramatic structural vibration emerges for α in the range of 6º − 8º because of the occurrence of the flutter. As α is increased to stall angle (α = 10º), a rapid drop is observed in the RMS value of lift, drag and displacement. Beyond the stall angle, the fluctuation of lift and drag forces increases slowly with α in the range of 14º < α < 50º while the vibration of the displacement hardly changes. In this range, one pronounced peak corresponding to the vortex shedding occurs in their spectral coherences. As α overs 60º, the fluctuations in lift, drag and structural response are impaired, becoming negligibly small. The peak associated with vortex shedding in the spectral coherences is not distinct.
KW - Flexible structure
KW - Fluid–structure interaction
KW - High-aspect-ratio wing
UR - https://www.scopus.com/pages/publications/85106446424
U2 - 10.1007/978-981-33-4960-5_53
DO - 10.1007/978-981-33-4960-5_53
M3 - 会议稿件
AN - SCOPUS:85106446424
SN - 9789813349599
T3 - Lecture Notes in Mechanical Engineering
SP - 353
EP - 358
BT - Fluid-Structure-Sound Interactions and Control - Proceedings of the 5th Symposium on Fluid-Structure-Sound Interactions and Control
A2 - Braza, Marianna
A2 - Hoarau, Yannick
A2 - Zhou, Yu
A2 - Lucey, Anthony D.
A2 - Huang, Lixi
A2 - Stavroulakis, Georgios E.
PB - Springer Science and Business Media Deutschland GmbH
T2 - 5th Symposium on Fluid-Structure-Sound Interactions and Control, FSSIC 2019
Y2 - 27 August 2019 through 30 August 2019
ER -