Reference : A Full Potential Static Aeroelastic Solver for Preliminary Aircraft Design
Scientific congresses and symposiums : Paper published in a book
Engineering, computing & technology : Aerospace & aeronautics engineering
http://hdl.handle.net/2268/237955
A Full Potential Static Aeroelastic Solver for Preliminary Aircraft Design
English
Crovato, Adrien mailto [Université de Liège - ULiège > Département d'aérospatiale et mécanique > Interactions Fluide-Structure - Aérodynamique expérimentale >]
Boman, Romain mailto [Université de Liège - ULiège > Département d'aérospatiale et mécanique > Département d'aérospatiale et mécanique >]
Güner, Hüseyin mailto [Université de Liège - ULiège > Département d'aérospatiale et mécanique > Interactions Fluide-Structure - Aérodynamique expérimentale >]
Dimitriadis, Grigorios mailto [Université de Liège - ULiège > Département d'aérospatiale et mécanique > Interactions Fluide-Structure - Aérodynamique expérimentale >]
Terrapon, Vincent mailto [Université de Liège - ULiège > Département d'aérospatiale et mécanique > Modélisation et contrôle des écoulements turbulents >]
Almeida, Hugo mailto [Embraer S.A. > > > >]
Prado, Alex mailto [Embraer S.A. > > > >]
Breviglieri, Carlos mailto [Embraer S.A. > > > >]
Cabral, Pedro mailto [Embraer S.A. > > > >]
Silva, Gustavo mailto [DLR German Aerospace Center > > > >]
2019
Proceedings of the 18th International Forum on Aeroelasticity and Structural Dynamics (IFASD2019)
No
International
18th International Forum on Aeroelasticity and Structural Dynamics
from 9-06-2019 to 13-06-2019
Savannah
United States of America
[en] Aeroelasticity ; Aerodynamics ; Transonic flow ; Full-Potential ; Aircraft Design
[en] There is a consensus in the aerospace research community that future aircraft will be more flexible and their wings will be more highly loaded. While this development is likely to increase aircraft efficiency, it poses several aeroelastic questions. Current aeroelastic tailoring practice for early preliminary aircraft design relies on linear aerodynamic modeling, unable to predict shocks. On the other hand, nonlinear solvers, although they provide a wide range of functionality and are reliable, often consist in monolithic code structures and cannot be efficiently coupled to external structural mechanics codes. They are therefore usually not readily usable for coupled fluid-structure interaction computations.
The objective of the present work is to carry out aerodynamic and static aeroelastic computations in the context of preliminary aircraft design. To this end, an open-source, fast and reliable, unstructured finite element, Full Potential solver has been developed. Preliminary results are presented and show a significant improvement over the classical linear potential method and are in good agreement with higher fidelity nonlinear solvers.
Aérospatiale et Mécanique - A&M
http://hdl.handle.net/2268/237955

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