Reference : Novel Instrumentation for the Measurement of the Unsteady Pressure Distribution aroun...
Scientific congresses and symposiums : Paper published in a book
Engineering, computing & technology : Aerospace & aeronautics engineering
http://hdl.handle.net/2268/24490
Novel Instrumentation for the Measurement of the Unsteady Pressure Distribution around a Wing Undergoing Stall Flutter Oscillations
English
Li, Jing [University of Manchester > School of Mechanical Aerospace and Civil Engineering > > >]
Dimitriadis, Grigorios mailto [Université de Liège - ULiège > Département d'aérospatiale et mécanique > Interactions Fluide-Structure - Aérodynamique expérimentale >]
Gu, Fengshu [University of Manchester > School of Mechanical Aerospace and Civil Engineering > > >]
Chen, Q. [Sinocera Piezotronics Inc, China > > > >]
Oct-2007
Autumn Conference of the Institute of Acoustics 2007: Advances in Noise and Vibration Engineering
Institute of Acoustics
Proceedings of the Institute of Acoustics, Volume 29, Part 5
27-41
No
No
International
1 901656 87 X
St Albans
United Kingdom
Autumn Conference of the Institute of Acoustics 2007: Advances in Noise and Vibration Engineering
du 17 octobre au 18 octobre 2007
Institute of Acoustics, United Kingdom
Oxford
United Kingdom
[en] Stall flutter ; Nonlinear Aeroelasticity ; Pressure Sensors
[en] In this work, a wind tunnel model of a wing undergoing stall flutter oscillations is studied. It is a rectangular wing with pitch and plunge degrees of freedom and low pitch stiffness. The objective of this study is to promote the understanding of the stall flutter phenomenon by measuring the unsteady pressure distribution around the wing as well as the wing displacement, during unforced motion in two degrees of freedom. Both steady and unsteady pressures must be measured with sufficient accuracy during two types of tests. In the static tests the wing is to be clamped in position and not allowed to move and the steady pressures are to be measured around the centre-span section at different angles of attack. Thus the stall angle of attack can be identified and the stall mechanism characterized. In the dynamic tests the wing will be allowed to move and the unsteady pressures will be measured and recorded during a number of cycles of the oscillation, at a number of free stream airspeeds.
Researchers ; Professionals
http://hdl.handle.net/2268/24490

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