The LAVA Computational Fluid Dynamics Solver

Kiris, Cetin C.; Barad, Michael F.; Housman, Jeffrey A.; Sozer, Emre; Brehm, Christoph; Moini-Yekta, Shayan

doi:10.2514/6.2014-0070

Cited by 53 publications

(33 citation statements)

References 49 publications

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“…While advantages and drawbacks of each approach have been heavily debated in the CFD community, 1, 2 the current authors feel that no clear "best" choice emerges. Since this study is targeted towards the Launch Vehicle and Ascent Aerodynamics (LAVA) CFD solver, [3][4][5] the focus will be limited to a cell-centered, finite-volume scheme. Gradient operator choice for an unstructured solver has a strong impact on accuracy, efficiency and robustness.…”

Section: Introductionmentioning

confidence: 99%

Gradient Calculation Methods on Arbitrary Polyhedral Unstructured Meshes for Cell-Centered CFD Solvers

Sozer¹,

Brehm

Kiris

2014

52nd Aerospace Sciences Meeting

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A survey of gradient reconstruction methods for cell-centered data on unstructured meshes is conducted within the scope of accuracy assessment. Formal order of accuracy, as well as error magnitudes for each of the studied methods, are evaluated on a complex mesh of various cell types through consecutive local scaling of an analytical test function. The tests highlighted several gradient operator choices that can consistently achieve 1 st order accuracy regardless of cell type and shape.The tests further offered error comparisons for given cell types, leading to the observation that the "ideal" gradient operator choice is not universal. Practical implications of the results are explored via CFD solutions of a 2D inviscid standing vortex, portraying the discretization error properties. A relatively naive, yet largely unexplored, approach of local curvilinear stencil transformation exhibited surprisingly favorable properties.

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Section: Introductionmentioning

confidence: 99%

Gradient Calculation Methods on Arbitrary Polyhedral Unstructured Meshes for Cell-Centered CFD Solvers

Sozer¹,

Brehm

Kiris

2014

52nd Aerospace Sciences Meeting

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“…LAVA provides additional modules for acoustic far-field propagation and scattering, conjugate heat transfer, and computational structural dynamics. For more details about the LAVA computational framework the reader is referred to Cetin et al 13 For the work presented in this paper, LAVA-Cartesian is utilized standalone to solve the compressible Navier-Stokes equations in conservative form considering an ideal, Newtonian, non-reactive gas. LAVACartesian is a block-structured, Immersed Boundary (IB) solver module with Adapative Mesh Refinement (AMR).…”

Section: A Lava Block-structured Cartesian Solvermentioning

confidence: 99%

“…These methods were first introduced as a nontraditional approach for numerically solving initial/boundary-value problems for complex geometries on Cartesian meshes and have matured to become increasingly important for a wide range of applications. [13][14][15] In the current paper, a higher-order sharp immersed boundary method is utilized. The IBM employed for solving the compressible Navier-Stokes equations was discussed in detail in Brehm et al 16 The approach is similar to that described by Li and Ito.…”

Section: Introductionmentioning

confidence: 99%

An Immersed Boundary Method for Solving the Compressible Navier-Stokes Equations with Fluid-Structure Interaction

Brehm

Barad

Kiris

2016

34th AIAA Applied Aerodynamics Conference

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An immersed boundary method for the compressible Navier-Stokes equation and the additional infrastructure that is needed to solve moving boundary problems and fully coupled fluid-structure interaction is described. All the methods described in this paper were implemented in NASA's LAVA solver framework. The underlying immersed boundary method is based on the locally stabilized immersed boundary method that was previously introduced by the authors. In the present paper this method is extended to account for all aspects that are involved for fluid structure interaction simulations, such as fast geometry queries and stencil computations, the treatment of freshly cleared cells, and the coupling of the computational fluid dynamics solver with a linear structural finite element method. The current approach is validated for moving boundary problems with prescribed body motion and fully coupled fluid structure interaction problems in 2D and 3D. As part of the validation procedure, results from the second AIAA aeroelastic prediction workshop are also presented. The current paper is regarded as a proof of concept study, while more advanced methods for fluid structure interaction are currently being investigated, such as geometric and material nonlinearities, and advanced coupling approaches.

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“…Evolved from ARC2D/3D in mid-1980s (discussed more later in this report). -LAVA: Launch Ascent and Vehicle Aerodynamics framework with versatile grid and multi-physics capability (Kiris et al, 2014) Incompressible Navier-Stokes codes: -INS3D family of codes: Incompressible Navier-Stokes flow solver (Kwak et al 1986). For more comprehensive discussion see Kwak and Kiris (2010).…”

Section: Compressible Euler and Navier-stokes Codesmentioning

confidence: 99%

“…This versatile capability is in need especially to support launch vehicle design, testing and operations. The Launch Ascent and Vehicle Aerodynamics (LAVA) framework is developed (Kiris et al, 2014) to provide versatility in grid/geometry modeling, fast turn around, and multi-physics capability. The LAVA framework essentially includes modules that can handle CFD, Conjugate Heat Transfer (CHT) and Computational Aero-Acoustics (CAA), and extended capabilities are being added.…”

Section: Lavamentioning

confidence: 99%