[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.
Disciplines :
Aerospace & aeronautics engineering
Author, co-author :
Li, Jing; University of Manchester > School of Mechanical Aerospace and Civil Engineering
Dimitriadis, Grigorios ; Université de Liège - ULiège > Département d'aérospatiale et mécanique > Interactions Fluide-Structure - Aérodynamique expérimentale
Language :
English
Title :
Experimental Study of Stall-Induced LCOs of Free Vibrating Wing
Publication date :
June 2007
Event name :
International Forum on Aeroelasticity and Structural Dynamics, IFASD 2007
Event organizer :
Council of European Aerospace Sciences, American Institute of Aeronautics and Astronautics
Event place :
Stockholm, Sweden
Event date :
du 18 juin au 20 juin 2007
Audience :
International
Main work title :
Proceedings of the 2007 International Forum on Aeroelasticity and Structural Dynamics
