Application of Navier–Stokes simulations for aeroelastic stability assessment in transonic regime

Cavagna, Luca; Quaranta, Giuseppe; Mantegazza, Paolo

doi:10.1016/j.compstruc.2007.01.005

Cited by 51 publications

(18 citation statements)

References 37 publications

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“…The steady and unsteady CFD computations with deformable meshes that account for the aircraft shape changes are performed using an Arbitrary Lagrangian Eulerian (ALE) formulation, as detailed in Cavagna et al (2007), where are detailed also the algorithms used to modify the CFD meshes based on the elastic analogy of the mesh with a continuum. The numerical procedures adopted to solve the problems related to each block of Fig.…”

Section: àmentioning

confidence: 99%

“…However, several authors (e.g. Raveh, 2004Raveh, , 2005Cavagna et al, 2007) showed that while the computation of the steady-state flow field is highly nonlinear, the response of the unsteady aerodynamic forces to small perturbations about it can be considered linear, often with a high level of accuracy for flutter prediction. So, also the flutter in the transonic regime is a problem that falls within the same class as the one already considered for the T-tail, i.e.…”

Section: Introductionmentioning

confidence: 99%

“…Here, it is proposed to tackle together the T-tail and transonic dependency of flutter stability problems on the equilibrium state by means of a unified framework based on computational fluid dynamics (CFD) coupled with computational structural dynamics (CSD), following the same numerical approach presented in Cavagna et al (2007). Several strategies can be used to address the flutter problem using CFD.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Aircraft T-tail flutter predictions using computational fluid dynamics

Attorni

Cavagna

Quaranta

2011

Journal of Fluids and Structures

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Section: àmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Aircraft T-tail flutter predictions using computational fluid dynamics

Attorni

Cavagna

Quaranta

2011

Journal of Fluids and Structures

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“…In order to determine the dynamic derivatives, a Reduced Order Model process has been implemented 19 ; it consists in a linear transfer matrix in the frequency domain which comes from numerical experiments in the time domain. A step input is given in terms of boundary motion (rigid or deformable), then the responses are computed (body forces or generalized forces) and Fast Fourier Transformed (FFT).…”

Section: Edge+rommentioning

confidence: 99%

Benchmarking the Prediction of Dynamic Derivatives: Wind Tunnel Tests, Validation, Acceleration Methods

Mialon¹,

Храбров²,

Ronch

et al. 2010

AIAA Atmospheric Flight Mechanics Conference

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The dynamic derivatives are widely used in linear aerodynamic models which are considered to determine the flying qualities of an aircraft: the ability to predict them reliably, quickly and sufficiently early in the design process is more and more important, in order to avoid late and costly component redesigns. This paper describes some experimental and computational activities dealing with the determination of dynamic derivatives. The work has been carried out within the FP6 European project SimSAC. Numerical and experimental results are compared for two aircraft configurations: the generic civil transport aircraft, wing-fuselage-tail configuration DLR-F12 and a generic Transonic CRuiser (TCR), which is a canard configuration. Static and dynamic wind tunnel tests have been carried out for both configurations and are briefly described. The data base generated for the DLR-F12 configuration includes force and pressure coefficients obtained during small amplitude pitch, roll and yaw oscillations while the data base for the TCR configuration includes force coefficients for small amplitude oscillations, dedicated to the determination of dynamic derivatives, and large amplitude oscillations, in order to investigate the dynamic effects on nonlinear aerodynamic characteristics. The influence of the canard has been investigated too. Dynamic derivatives have been determined on both configurations with a large panel of tools, from linear aerodynamic (Vortex Lattice Methods) to CFD (unsteady Reynolds-Averaged Navier-Stokes solvers). The study confirms that an increase in fidelity level enables dynamic derivatives to be better calculated. Linear aerodynamics (VLM) tools can give satisfactory results but are very sensitive to the geometry/mesh input data. Although all the quasi-steady CFD approaches give very comparable results (robustness) on steady dynamic derivatives, they do not allow the prediction of unsteady components of the dynamic derivatives (angular derivatives w.r.t. time): this can be done with either a fully unsteady approach (with a time-marching scheme) or with Frequency Domain solvers, both of them giving very comparable results for the DLR-F12 test case. As far as the canard configuration is concerned; strong limitations of linear aerodynamic tools are observed. A specific attention is paid to acceleration techniques in CFD methods, which allow the computational time to be dramatically reduced while keeping a satisfactory accuracy.

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“…Recently a number of numerical simulations have been made in order to assess the aeroelastic behaviour of bridge structures. The most advanced ones take into account the three-dimensional motion of a bridge deck in fluid flow [5,22]. This approach is rare nowadays, mainly because it is computationally intensive.…”

Section: Introductionmentioning

confidence: 99%

Numerical simulation of the flutter performance of different generic bridge cross sections

Szabó¹,

Györgyi²

2011

Per. Pol. Civil Eng.

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This paper presents the results of numerical simulation of the flutter performance of different generic bridge cross sections. The bridge flutter assessment has become a major concern in bridge design practice. In the early ages, wind tunnel tests were made in order to assess the aerodynamic performance of bridges. In this paper the flutter performance of different bridge deck sections was investigated by using numerical flow simulation. The detailed comparison of the aerodynamic behaviour of the different cross sections in terms of flutter instability gives the engineers good means to design of bridge structures. KeywordsBridge deck flutter · aeroelasticity · critical wind speed Acknowledgement The authors are grateful for the support

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Application of Navier–Stokes simulations for aeroelastic stability assessment in transonic regime

Cited by 51 publications

References 37 publications

Aircraft T-tail flutter predictions using computational fluid dynamics

Aircraft T-tail flutter predictions using computational fluid dynamics

Benchmarking the Prediction of Dynamic Derivatives: Wind Tunnel Tests, Validation, Acceleration Methods

Numerical simulation of the flutter performance of different generic bridge cross sections

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