Reference : Aeroelastic System Identification using Transonic CFD data for a 3D Wing
Scientific congresses and symposiums : Paper published in a book
Engineering, computing & technology : Aerospace & aeronautics engineering
http://hdl.handle.net/2268/23144
Aeroelastic System Identification using Transonic CFD data for a 3D Wing
English
Vio, Gareth Arthur [University of Manchester > School of Mechanical Aerospace and Civil Engineering > > >]
Cooper, Jonathan Edward [University of Manchester > School of Mechanical Aerospace and Civil Engineering > > >]
Dimitriadis, Grigorios mailto [Université de Liège - ULiège > Département d'aérospatiale et mécanique > Intéractions fluide structure et aérodynamique expérimentale >]
Badcock, Ken [University of Liverpool > Department of Engineering > > >]
Woodgate, Marc [University of Liverpool > Department of Engineering > > >]
Rampurawala, Abdul [University of Liverpool > Department of Engineering > > >]
Jul-2006
Proceedings of the IX International Conference on Recent Advances in Structural Dynamics
Brennan, M. J.
Liguore, S.
Mace, B. R.
Muggleton, J. M.
Murphy, K. D.
Petersson, B. A. T.
Rizzi, S. A.
Shen, R.
Institute of Sound and Vibration
Paper 38
Yes
No
International
0-854-32-8475
Southampton
United Kingdom
9th International Conference on Recent Advances in Structural Dynamics
du 17 juillet 2009 au 19 juillet 2009
Institute of Sound and Vibration, University of Southampton
Southampton
United Kingdom
[en] Aeroelasticity ; CFD ; System Identification
[en] This paper is part of a study investigating the prediction of aeroelastic behaviour subjected to
non-linear aerodynamic forces. Of interest here is whether the sub-critical vibration behaviour
of the aeroelastic model gives any information about the onset of the LCO. It would be useful to
be able to use system identification methods to estimate aeroelastic models that characterise the
LCO. Such a methodology would be very useful, not only for analysis with coupled CFD/FE
models, but also during flight flutter testing.
In this paper, the responses to initial inputs on the Goland Wing [9] CFD/FE model at different
flight speeds are analysed to determine the extent of the non-linearity below the critical onset of
LCO. Analysis is also performed using a linear identification model.
Researchers ; Professionals
http://hdl.handle.net/2268/23144

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