Reference : Flutter and stall flutter of a rectangular wing in a wind tunnel
Scientific journals : Article
Engineering, computing & technology : Aerospace & aeronautics engineering
http://hdl.handle.net/2268/84929
Flutter and stall flutter of a rectangular wing in a wind tunnel
English
Norizham, Abdul Razak mailto [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 >]
2011
AIAA Journal
American Institute of Aeronautics and Astronautics
49
10
2258-2271
Yes (verified by ORBi)
International
0001-1452
Reston
VA
[en] Aeroelasticity ; Stall flutter ; Limit Cycle Oscillation ; Bifurcation
[en] The aeroelastic behavior of a rectangular wing with pitch and plunge degrees of freedom was observed experimentally using pressure, acceleration and PIV measurements. The wing was set at different static angles of attack and wind tunnel airspeeds. The wing's dynamic behavior was governed by a two-parameter bifurcation from steady to Limit Cycle Oscillations (LCO), the two parameters being the airspeed and the static angle of attack. At the lowest static angle, the wing underwent a classical flutter phenomenon that was transformed into a supercritical Hopf bifurcation at higher angles. The latter was combined with a fold bifurcation at intermediate angles of attack.

All LCOs observed were either low amplitude oscillations with time-varying amplitude or high amplitude oscillations with nearly steady amplitude. They were caused by two different types of dynamic stall phenomena. During low amplitude LCOs the periodically stalled flow covered only the rear part of the wing. During high amplitude LCOs, trailing edge and leading edge separation occured. Trailing edge separation was characterized by a significant amount of unsteadiness, varying visibly from cycle to cycle. The occurrence of leading edge separation was much more regular and had the tendency to stabilize the amplitude of the LCO motion.
Researchers ; Professionals
http://hdl.handle.net/2268/84929

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