Progress in Computational Flow-Structure Interaction

Haase, Werner|Selmin, Vittorio|Winzell, Bengt

ISBN 10: 3540439021 / ISBN 13: 9783540439028

Edité par Springer Berlin Heidelberg, 2002

A propos de cet article

Dieser Artikel ist ein Print on Demand Artikel und wird nach Ihrer Bestellung fuer Sie gedruckt. State of the art in computational fluid dynamics and nonlinear aeroelasticityState of the art in computational fluid dynamics and nonlinear aeroelasticityIncludes supplementary material: sn.pub/extrasAircraft design processes require e.

N° de réf. du vendeur 4890719

Détails bibliographiques

• Titre: Progress in Computational Flow-Structure Interaction
• Éditeur: Springer Berlin Heidelberg
• Date de parution: 2002
• Langue: anglais
• ISBN à 10 chiffres: 3540439021
• ISBN à 13 chiffres: 9783540439028
• Reliure: Couverture rigide
• État de l'article: New
• Catalogues du vendeur:
  • Mathematik/Naturwissenschaften/Technik/Medizin

A propos de ce titre

Synopsis

Aircraft design processes require extensive work in the area of both aerodynamics and structure, fonning an environment for aeroelasticity investigations. Present and future designs of European aircraft are characterized by an ever increasing aircraft size and perfonnance. Strong weight saving requirements are met by introduction of new materials, leading to more flexible structure of the aircraft. Consequently, aeroelastic phenomena such as vortex-induced aeroelastic oscillations and moving shock waves can be predominant and may have a significant effect on the aircraft perfonnance. Hence, the ability to estimate reliable margins for aeroelastic instabilities (flutter) or dynamic loads (buffeting) is a major concern to the aircraft designer. As modern aircrafts have wing bending modes with frequencies that are low enough to influence the flight control system, demands on unsteady aerodynamics and structural analysis to predict flight control effectiveness and riding comfort for passengers are extremely high. Therefore, the aircraft industries need an improved capacity of robust, accurate and reliable prediction methods in the coupled aeroelastic, flight mechanics and loads disciplines. In particular, it is necessary to develop/improve and calibrate the numerical tools in order to predict with high level of accuracy and capability complex and non-classical aeroelastic phenomena, including aerodynamic non-linearities, such as shock waves and separation, as well as structural non-linearities, e. g. control surface free-play. Nowadays, robust methods for structural analysis and linearised unsteady aerodynamics are coupled and used by the aircraft industry to computationally clear a new design from flutter.