ORBi: Li Jing - Experimental Study of Stall-Induced LCOs of Free Vibrating Wing

Reference : Experimental Study of Stall-Induced LCOs of Free Vibrating Wing


	Document type :	Scientific congresses and symposiums : Paper published in a book
	Discipline(s) :	Engineering, computing & technology : Aerospace & aeronautics engineering
	To cite this reference:	http://hdl.handle.net/2268/24605

Title :	Experimental Study of Stall-Induced LCOs of Free Vibrating Wing
Language :	English
Author, co-author :	Li, Jing [University of Manchester > School of Mechanical Aerospace and Civil Engineering > > >]
	Dimitriadis, Grigorios [Université de Liège - ULg > Département d'aérospatiale et mécanique > Interactions Fluide-Structure - Aérodynamique expérimentale >]
Publication date :	Jun-2007
Main document title :	Proceedings of the 2007 International Forum on Aeroelasticity and Structural Dynamics
Publisher :	KTH
Pages :	Paper IF-026-LI-LCO
On invitation :	No
Audience :	International
City :	Stockholm
Country :	Sweden
Event name :	International Forum on Aeroelasticity and Structural Dynamics, IFASD 2007
Event date :	du 18 juin au 20 juin 2007
Event organizer :	Council of European Aerospace Sciences, American Institute of Aeronautics and Astronautics
Event place (city) :	Stockholm
Event country :	Sweden
Keywords :	[en] Nonlinear Aeroelasticty ; Stall flutter ; Dynamic Stall
Abstract :	[en] Stall flutter is a limit cycle oscillation phenomenon occurring when all or part of the flow over a wing separates and re-attaches periodically. This paper reports on experimental investigations carried out on the subsonic stall flutter of a pitch plunge wing wind tunnel model. The object of the experiments was to investigate the aeroelastic effects of the nonlinearity introduced by boundary layer growth and flow separation and the ensuing stall-induced flutter, on a freely vibrating aeroelastic system. The motion of the wing and the pressure distribution around its surface were measured at various conditions. Three types of motion were observed, sometimes at the same wind tunnel airspeed; decay to equilibrium, symmetric limit cycle oscillations (LCO) and asymmetric LCOs. The aerodynamic mechanisms that give rise to these LCOs are described and analyzed. The effect of torsional wing stiffness on the stall flutter response of the wing is also investigated. Finally, repeating the experiments in a smaller wind tunnel showed that wind tunnel blockage has a significant effect on stall flutter.
Target :	Researchers ; Professionals
Permalink :	http://hdl.handle.net/2268/24605

File(s) associated to this reference

Fulltext file(s):

	File	Commentary	Version	Size	Access
Restricted access	31 IF-026-LI-LCO.pdf		Publisher postprint	885.37 kB	Request copy

All documents in ORBi are protected by a user license.

Dspace v1.5