Parallelisation of a Gridfree Kinetic Upwind Solver

Anandhanarayanan, K.; Nagarathinam, M.

doi:10.2514/6.2005-4628

Cited by 5 publications

(4 citation statements)

References 3 publications

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“…The FPM method used a polynomial basis, echoing themes from the classical finite element method. Least squares methods based on Taylor series expansions have been used extensively by Deshpande and others [7][8][9][10][11][12][13][14][15] in the context of kinetic schemes for the Euler equations. They have developed extensive capabilities with the least squares kinetic upwind method (LSKUM).…”

Section: Introductionmentioning

confidence: 99%

A Comparison of Various Meshless Schemes Within a Unified Algorithm

Jameson

2009

47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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An algorithm for use with several meshless schemes is presented based on a local extremum diminishing property. The scheme is applied to the Euler equations in two dimensions. The algorithm is suitable for use with many meshless schemes, three of which are detailed here. First, a method based on Taylor series expansion and least squares is highlighted. Next, a similar least squares method is used, but using polynomial basis functions with fixed Gaussian weighting. A third method makes use of the Hardy multiquadric radial basis functions on a local cloud of points. Results indicate that all three methods perform essentially equally well for flows without shocks. For flows with shocks, the least squares methods perform significantly better than the radial basis method, which displays discrepancies in shock location and magnitude. All methods are compared to an established finite volume method for validation purposes.

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Section: Introductionmentioning

confidence: 99%

A Comparison of Various Meshless Schemes Within a Unified Algorithm

Jameson

2009

47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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“…Kinetic characteristic boundary condition (KCBC) and kinetic outer boundary condition (KOBC) [12] are implemented for treating wall and far-field boundaries, respectively. The q-LSKUM Euler solver is parallelized in the message passing interface (MPI) environment to run on distributed computing systems [13]. The flow solver has been verified against standard test cases and validated [14].…”

Section: Grid-free Euler Solvermentioning

confidence: 99%

Estimation of Captive Flight Loads Using Grid-Free Euler Solver

Shah

Raju

et al. 2011

Journal of Aircraft

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The structural integrity of a store and its attachments to a fighter aircraft has to be verified at various aircraft maneuvering conditions in its flight envelope for the clearance of the store to integrate with aircraft. The captive loads of a flight vehicle mounted on a fighter aircraft have been estimated at various Mach numbers, angles of attack, and sideslip angles using an indigenously developed 3-D grid-free Euler solver. The point distributions required to apply grid-free solver are obtained using chimera cloud technique, and the connectivity required for the solver is obtained using gradient search method. Forces and moments acting on the fighter aircraft with launchers and flight vehicles have been estimated using computational fluid dynamics simulations at different flow conditions, and load distributions on flight vehicle have been obtained. The aerodynamic loads obtained from computational fluid dynamics calculations form the basis of the flight testing.

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“…Among those methods, LSKUM and q-LSKUM have been applied on various distributions of points [11][12][13][14] and have solved number of complex fluid problems [15][16][17][18] . A 3-D grid-free Euler code based on q-LSKUM has been developed 19 ; lower-upper symmetric gauss Seidel 20 has been implemented in q-LSKUM code 21 to get faster convergence and the code has been parallelised using message passing interface (MPI) to run on cluster/parallel computers 22 . The code has been thoroughly verified and validated for various complex flight vehicle configurations, from subsonic to hypersonic flows 17 .…”

Section: Introductionmentioning

confidence: 99%

Development of Three-dimensional Grid-free Solver and its Applications to Multi-body Aerospace Vehicles

Anandhanarayanan

2010

DSJ

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Grid-free solver has the ability to solve complex multi-body industrial problems with minimal effort. Grid-free Euler solver has been applied to number of multi-body aerospace vehicles using Chimera clouds of points including flight vehicle with fin deflection, nose fairing separation of hypersonic launch vehicle. A preprocessor has been developed to generate connectivity for multi-bodies using overlapped grids. Surface transpiration boundary condition has been implemented to model aerodynamic damping and to impose the relative velocity of moving components. Dynamic derivatives are estimated with reasonable accuracy and less effort using the grid-free Euler solver with the transpiration boundary condition. Further, the grid-free Euler solver has been integrated with six-degrees of freedom (6-DOF) equations of motion to form store separation dynamics suite which has been applied to obtain the trajectory of a rail launch air-to-air-missile from a complex fighter aircraft.

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Parallelisation of a Gridfree Kinetic Upwind Solver

Cited by 5 publications

References 3 publications

A Comparison of Various Meshless Schemes Within a Unified Algorithm

A Comparison of Various Meshless Schemes Within a Unified Algorithm

Estimation of Captive Flight Loads Using Grid-Free Euler Solver

Development of Three-dimensional Grid-free Solver and its Applications to Multi-body Aerospace Vehicles

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