Journal ArticleDOI
Aeroelastic calculations for the hawk aircraft using the euler equations
TLDR
In this paper, coupled time-domain computational-fluid-dynamics (CFD) and computationalstructural-Dynamics simulations for flutter analysis of a real aircraft in the transonic regime are presented.Abstract:
This paper demonstrates coupled time-domain computational-fluid-dynamics (CFD) and computationalstructural-dynamics simulations for flutter analysis of a real aircraft in the transonic regime. It is shown that a major consideration for a certain class of structural models is the transformation method, which is used to pass information between the fluid and structural grids. The aircraft used for the calculations is the BAE Systems Hawk. A structural model, which has been developed by BAE Systems for simplified linear flutter calculations, only has a requirement for O(10) degrees of freedom. There is a significant mismatch between this and the surface grid on which loads and deflections are defined in the CFD calculation. This paper extends the constant volume tetrahedron tranformation, previously demonstrated for wing-only aeroelastic calculations, to multicomponent, or full aircraft, cases and demonstrates this for the Hawk. A comparison is made with the predictions of a linear flutter code.read more
Citations
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Journal ArticleDOI
Unified fluid-structure interpolation and mesh motion using radial basis functions
Thomas Rendall,Christian B Allen +1 more
TL;DR: In this paper, a multivariate interpolation scheme, using radial basis functions, is presented, which results in a completely unified formulation for the fluid-structure interpolation and mesh motion problems.
Journal ArticleDOI
Non-linear aeroelastic prediction for aircraft applications
M. J. de C. Henshaw,Ken Badcock,Gareth A. Vio,Christian B Allen,J. Chamberlain,I. Kaynes,Grigorios Dimitriadis,Jonathan E. Cooper,Mark Woodgate,Abdul Rampurawala,Dorian P Jones,CL Fenwick,Ann L Gaitonde,NV Taylor,D. S. Amor,T. A. Eccles,C. J. Denley +16 more
TL;DR: A thorough review of the PUMA aeroelastics programme is presented, which has provided a suite of methods that allow realistic consideration of non-linear behaviour to be modelled, but at a cost comparable with that of the regular linear methods.
Journal ArticleDOI
Fast prediction of transonic aeroelastic stability and limit cycles
Mark Woodgate,Ken Badcock +1 more
TL;DR: In this article, the authors used Hopf bifurcation and center manifold theory to compute flutter speeds and limit-cycle responses of wings in transonic flow when the aerodynamics are modeled by the Euler equations.
Proceedings ArticleDOI
Unified Approach to CFD-CSD Interpolation and Mesh Motion using Radial Basis Functions
Christian B Allen,Thomas Rendall +1 more
Journal ArticleDOI
Transonic Aeroelastic Stability Predictions Under the Influence of Structural Variability
TL;DR: In this paper, an eigenvalue-based stability method together with Euler-level aerodynamics and different methods for propagating structural variability to stability predictions are presented for the Goland wing and a generic fighter configuration.
References
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Towards the ultimate conservative difference scheme. II. Monotonicity and conservation combined in a second-order scheme
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Proceedings ArticleDOI
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Journal ArticleDOI
Two efficient staggered algorithms for the serial and parallel solution of three-dimensional nonlinear transient aeroelastic problems
Charbel Farhat,Michel Lesoinne +1 more
TL;DR: This paper proposes two alternative serial and parallel staggered algorithms for the solution of coupled transient aeroelastic problems, and demonstrates their superior accuracy and computational efficiency with the flutter analysis of the AGARD Wing 445.6.
Journal ArticleDOI
Geometric conservation laws for flow problems with moving boundaries and deformable meshes, and their impact on aeroelastic computations
Michel Lesoinne,Charbel Farhat +1 more
TL;DR: In this paper, a unified theory for deriving Geometric conservation laws (GCLs) for flow problems with moving boundaries is presented, and the impact of these constraints on the solution of coupled aeroelastic problems, and highlight the importance of the GCLs with an illustration of their effect on the computation of a flat panel in transonic flow.