Reference : Theoretical and experimental investigation of a structurally and aerodynamically nonl...
Scientific congresses and symposiums : Paper published in a book
Engineering, computing & technology : Aerospace & aeronautics engineering
http://hdl.handle.net/2268/183892
Theoretical and experimental investigation of a structurally and aerodynamically nonlinear pitch and flap wing
English
Verstraelen, Edouard mailto [Université de Liège > Département d'aérospatiale et mécanique > Laboratoire de structures et systèmes spatiaux >]
Boutet, Johan mailto [Université de Liège > Département d'aérospatiale et mécanique > Interactions Fluide-Structure - Aérodynamique expérimentale >]
Grappasonni, Chiara mailto [Université de Liège > Département d'aérospatiale et mécanique > Laboratoire de structures et systèmes spatiaux >]
Kerschen, Gaëtan mailto [Université de Liège > Département d'aérospatiale et mécanique > Laboratoire de structures et systèmes spatiaux >]
Dimitriadis, Grigorios mailto [Université de Liège > Département d'aérospatiale et mécanique > Interactions Fluide-Structure - Aérodynamique expérimentale >]
29-Jun-2015
Proceedings of the International Forum on Aeroelasticity and Structural Dynamics, IFASD 2015
Paper IFASD-2015-012
No
No
International
International Forum on Aeroelasticity and Structural Dynamics
from 28-06-2015 to 02-07-2015
Central Aerohydrodynamics Institute (TsAGI)
Saint Petersburg
Russia
[en] Nonlinear aeroelasticity ; Wind tunnel testing ; Dynamic stall ; Stall flutter ; Leishman-Beddoes
[en] This paper presents and experimental and theoretical investigation of a novel nonlinear aeroelastic system. It consists of a wing with pitch and flap degrees of freedom, suspended from a leaf spring secured in a nonlinear clamp. Both the structural and the aerodynamic forces acting on the wing can be nonlinear, depending on the amplitude of oscillations. Wind tunnel experiments show that the system undergoes a supercritical Hopf bifurcation that leads to small amplitude limit cycle oscillations. At a particular airspeed, the pitch amplitude jumps to a much higher value and dynamic stall starts to occur. Three mathematical models of the system are formulated, one based on linear aerodynamics
and two based on the Leishman-Beddoes dynamic stall model. The objective of the modelling is to determine whether the jump in pitch oscillation amplitude is due to dynamic stall. The predictions for amplitude, frequency and mean angle of the limit cycle oscillations are compared to the experimental observations. All three models predict the small amplitude oscillations with satisfactory accuracy. The complete Leishman-Beddoes model predicts the occurrence of a jump in pitch amplitude but the magnitude of this jump is signi cantly overestimated. The other two models completely fail to model the jump. The failure of the Leishman-Beddoes model to predict the correct post-jump oscillation amplitude may be due to the values selected for the model parameters.
European Union (ERC Starting Grant NoVib 307265)
The Nonlinear Tuned Vibration Absorber (NoVib)
Researchers ; Professionals
http://hdl.handle.net/2268/183892

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