Reference : Limit cycle oscillations of cantilever rectangular wings designed using topology opti...
Scientific congresses and symposiums : Paper published in a book
Engineering, computing & technology : Aerospace & aeronautics engineering
http://hdl.handle.net/2268/243090
Limit cycle oscillations of cantilever rectangular wings designed using topology optimisation
English
Munk, D. J. [Defence Science and Technology > Aerospace Division > > >]
Dooner, D. [University of Sydney > School of Aerospace, Mechanical and Mechatronic Engineering > > >]
Best, F. [University of Sydney > School of Aerospace, Mechanical and Mechatronic Engineering > > >]
Vio, G. A. [University of Sydney > School of Aerospace, Mechanical and Mechatronic Engineering > > >]
Giannelis, N. F. [Sydney > School of Aerospace, Mechanical and Mechatronic Engineering > > >]
Murray, A. J. [University of Sydney > School of Aerospace, Mechanical and Mechatronic Engineering > > >]
Dimitriadis, Grigorios mailto [Université de Liège - ULiège > Département d'aérospatiale et mécanique > Interactions Fluide-Structure - Aérodynamique expérimentale >]
Jan-2020
Proceeding of AIAA SciTech 2020 Forum
No
No
International
AIAA SciTech 2020 Forum and Exhibition
from 6-1-2020 to 11-1-2020
American Institute of Aeronautics and Astronautics
Orlando, Flordia
United States
[en] Limit Cycle Oscillation ; Topology Optimization ; Wind Tunnel
[en] A closed form state-space model for the nonlinear aeroelastic response of thin cantilevered flat plates is derived using a combination of von Karman thin plate theory and a linearized continuous time vortex lattice aerodynamic model. The modal-based model is solved for the amplitude and period of the limit cycles of the flat plates using numerical continuation. The resulting predictions are compared to experimental data obtained from identical flat plates in the wind tunnel. Both conventional and topologically optimised flat rectangular plates are investigated. It is shown that the aeroelastic model predicts the linear flutter conditions and nonlinear response of the plates with reasonable accuracy, although the predicted limit cycle amplitude variation with airspeed is different to the one measured experimentally due to unmodelled physics.
Researchers ; Professionals
http://hdl.handle.net/2268/243090
10.2514/6.2020-1907
https://arc.aiaa.org/doi/10.2514/6.2020-1907

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