Reference : Analysis of dynamic response of a very flexible Delta wing model in a wind tunnel
Scientific congresses and symposiums : Paper published in a book
Engineering, computing & technology : Aerospace & aeronautics engineering
http://hdl.handle.net/2268/24439
Analysis of dynamic response of a very flexible Delta wing model in a wind tunnel
English
Barbason, Mathieu mailto [Université de Liège - ULg > Département Argenco : Secteur TLU+C > Urbanisme et aménagement du territoire >]
Andrianne, Thomas mailto [Université de Liège - ULg > Département d'aérospatiale et mécanique > Département d'aérospatiale et mécanique >]
Hickey, Daryl [Université de Liège - ULg > Département d'aérospatiale et mécanique > Laboratoire des Systèmes Multicorps et Mécatroniques >]
Dimitriadis, Grigorios mailto [Université de Liège - ULg > Département d'aérospatiale et mécanique > Interactions Fluide-Structure - Aérodynamique expérimentale >]
Jul-2009
Proceedings of the 2009 International Forum on Aeroelasticity and Structural Dynamics
Azimuth Corporation
Paper IFASD-2009-139
No
No
International
Dayton, Ohio
USA
International Forum on Aeroelasticity and Structural Dynamics, IFASD 2009
du 21 juin au 25 juin 2009
Council of European Aerospace Sciences, American Institute of Aeronautics and Astronautics
Seattle, Washington
USA
[en] Aeroelasticity ; Limit Cycle Oscillations ; buffeting ; Delta wing
[en] Limit cycle oscillations involving Delta wings are an important area of
research in modern aeroelasticity. Such phenomena can be the result of geometric nonlin-
earity, aerodynamic nonlinearity or under-wing store nonlinearity. In this paper, a flexible
half-Delta wing without stores is tested in a low speed wind tunnel in order to investigate
its dynamic response. It is found that, at several combinations of airspeed and angle of
attack, the wing undergoes high amplitude limit cycle oscillations. Three types of such
oscillations are observed. Type 1 oscillations occur only at low angles of attack and are
the result of a Hopf-type bifurcation. Type 2 limit cycle oscillations occur at intermedi-
ate angles of attack and are the result of an atypical bifurcation. In other words, these
oscillations appear as the airspeed is increased but disappear at even higher airspeeds.
Type 3 oscillations occur at even higher angles of attack. A bispectrum analysis shows
that type 3 limit cycle oscillations feature quadratic phase coupling. No such coupling
was measured for type 2 oscillations, leading to the conclusion that the nonlinearity must
be of higher order.
Researchers ; Professionals
http://hdl.handle.net/2268/24439
http://papers.ifasd2009.com/proceedings

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