Calculation of Inviscid Transonic Flow over a Complete Aircraft

Jameson, Antony; Baker, Timothy J.; Weatherill, N. P.

doi:10.2514/6.1986-103

Cited by 313 publications

(144 citation statements)

References 10 publications

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“…This set of faces will be defined as Γ B a (see Figure 2b). By using this approach, the discretisation of the fluxes using centred differences is equivalent to a classical Bubnov Galerkin spatial discretisation with linear elements [72][73][74]. This type of dual mesh also allows for the computation of the gradients by means of the Green-Gauss approach [75].…”

Section: Dual Mesh and Area Vectorsmentioning

confidence: 99%

An upwind vertex centred Finite Volume solver for Lagrangian solid dynamics

Aguirre

Gil

Bonet

et al. 2015

Journal of Computational Physics

152

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A vertex centred Jameson-Schmidt-Turkel (JST) finite volume algorithm was recently introduced by the authors (Aguirre et al., 2014 [1]) in the context of fast solid isothermal dynamics. The spatial discretisation scheme was constructed upon a Lagrangian two-field mixed (linear momentum and the deformation gradient) formulation presented as a system of conservation laws [2][3][4]. In this paper, the formulation is further enhanced by introducing a novel upwind vertex centred finite volume algorithm with three key novelties. First, a conservation law for the volume map is incorporated into the existing two-field system to extend the range of applications towards the incompressibility limit (Gil et al., 2014 [5]). Second, the use of a linearised Riemann solver and reconstruction limiters is derived for the stabilisation of the scheme together with an efficient edge-based implementation. Third, the treatment of thermo-mechanical processes through a Mie-Grüneisen equation of state is incorporated in the proposed formulation. For completeness, the study of the eigenvalue structure of the resulting system of conservation laws is carried out to demonstrate hyperbolicity and obtain the correct time step bounds for non-isothermal processes. A series of numerical examples are presented in order to assess the robustness of the proposed methodology. The overall scheme shows excellent behaviour in shock and bending dominated nearly incompressible scenarios without spurious pressure oscillations, yielding second order of convergence for both velocities and stresses.

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Section: Dual Mesh and Area Vectorsmentioning

confidence: 99%

An upwind vertex centred Finite Volume solver for Lagrangian solid dynamics

Aguirre

Gil

Bonet

et al. 2015

Journal of Computational Physics

152

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“…The revised formula, which preserves the accuracy of the numerical solution, is written in the following to (Jameson et al, 1986).…”

Section: Discrete Formulationmentioning

confidence: 99%

Coupled solution of oil slick and depth averaged tidal currents on three-dimensional geometry of Persian Gulf

Yazdi

2005

Int. J. Environ. Sci. Technol.

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ABSTRACT:In this paper, simulation of oil spill due to tidal currents in Persian Gulf is performed by coupled solution of the hydrodynamics equations and an equation for convection and diffusion of the oil. The hydrodynamic equations utilized in this work consist of depth average equations of continuity and motion in two dimensional horizontal planes. The effect of evaporation is considered in the continuity equation and the effects of bed slope and friction, as well as the Coriolis effects are considered in two equations of motion. The overlapping cell vertex finite volume method is applied for solving the governing equations on triangular unstructured meshes. Using unstructured meshes provides great flexibility for modeling the flow in arbitrary and complex geometries, such as Persian Gulf flow domain. The results of the hydrodynamic model for tidal currents in Persian Gulf domain is examined by imposing tidal fluctuations to the main flow boundary during a limited period of time. Finally, the developed model is used to simulate an accidental oil spill from a point in Persian Gulf.

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“…References [18] and [19] present a method based on such an approach. Since an arbitrary set of points admits a triangulation, the problem can be simplified by separating the procedure for generating mesh points from the procedure for triangulating them.…”

Section: Airplane Calculationmentioning

confidence: 99%

“…Therefore, as new points are added, it is necessary to test for this eventuality, and whenever it occurs the reconnection is modified to preserve the integrity of the solid boundary. This approach to mesh generation has been combined with the finite element method outlined in Section 2 to perform flow calculations for complete aircraft [18,19]. Calculations with this number of mesh points require just under 12 million words of memory.…”

Section: Airplane Calculationmentioning

confidence: 99%