Reference : Bifurcation analysis of a wing undergoing stall flutter oscillations in a wind tunnel
Scientific congresses and symposiums : Paper published in a book
Engineering, computing & technology : Mechanical engineering
http://hdl.handle.net/2268/72153
Bifurcation analysis of a wing undergoing stall flutter oscillations in a wind tunnel
English
Norizham, Abdul Razak [Université de Liège - ULg > Département d'aérospatiale et mécanique > Interactions Fluide-Structure - Aérodynamique expérimentale >]
Andrianne, Thomas mailto [Université de Liège - ULg > Département d'aérospatiale et mécanique > Département d'aérospatiale et mécanique >]
Dimitriadis, Grigorios mailto [Université de Liège - ULg > Département d'aérospatiale et mécanique > Interactions Fluide-Structure - Aérodynamique expérimentale >]
20-Sep-2010
Proceedings of ISMA2010
Katholieke Universiteit Leuven
3587-3602
No
No
International
9789073802872
Leuven
Belgium
International Conference on Noise and Vibration Engineering (ISMA 2010)
from 20-09-2010 to 22-09-2010
Katholieke Universiteit Leuven
Leuven
Belgium
[en] Stall Flutter ; Flow Visualization ; Bifurcation
[en] Stall flutter is a Limit Cycle Oscillation (LCO) caused by the periodic separation of the flow around a wing immersed in a uniform fluid flow. The separation could be either partial or complete [1]. The work presented focuses on a wing undergoing stall flutter in the pitch degree of freedom. The phenomenon is analyzed from the structural and aerodynamic response perspectives. The objective of this study is to promote the understanding of stall flutter by characterizing the complete bifurcation behavior of the selected system. The wing section chosen for this study is NACA 0018 profile applied to a rectangular wing. The tests are carried out at different airspeeds and angles of attack. The measured aeroelastic responses are analyzed and the behavior of the dynamic system is characterized by fully describing its bifurcation. Structural accelerations as well as unsteady pressures around the mid-span point of the wing are measured and examined. Furthermore, flow field visualization by means of the Particle Image Velocimetry technique is used to demonstrate aspects of the unsteady flow field, such as the manifestation of separation and vortices.
Researchers ; Professionals
http://hdl.handle.net/2268/72153

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