Numerical Simulations of Shock/Plume Interaction Using Structured Overset Grids

Housman, Jeffrey A.; Kiris, Cetin C.

doi:10.2514/6.2015-2262

Cited by 10 publications

(2 citation statements)

References 16 publications

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“…In this study, the structured curvilinear overlapping grid CFD solver in LAVA is used to generate the near-field CFD solutions. It has been shown, 2,50 that structured overset grids are a good option for near-field steady-state RANS simulations of supersonic aircraft. The structured overlapping grids used in this work were generated using a combination of Pointwise 51 and the Chimera Grid Tools (CGT) software package.…”

Section: Resultsmentioning

confidence: 99%

Efficient Near-Field to Mid-Field Sonic Boom Propagation Using a High-Order Space Marching Method

Housman

Kenway²,

Jensen

et al. 2019

AIAA Aviation 2019 Forum

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An e cient strategy for propagating sonic boom signatures from a near-field Computational Fluid Dynamics (CFD) solution to the mid-field is presented. The method is based on a high-order accurate finite-di↵erence discretization of the 3D Euler equations on a specially designed curvilinear grid and a single sweep space marching solution algorithm. The new approach leads to more than a factor of two reduction in overall computational resources compared to the current method used to propagate near-field sonic booms to the ground. Accuracy and e ciency of the near-field to mid-field process is demonstrated using a selection of test cases from the AIAA Sonic Boom Prediction Workshops. Azimuthal dependence of nonlinear wave propagation from the near-field to mid-field is analyzed along with its e↵ects on the ground level noise.

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Section: Resultsmentioning

confidence: 99%

Efficient Near-Field to Mid-Field Sonic Boom Propagation Using a High-Order Space Marching Method

Housman

Kenway²,

Jensen

et al. 2019

AIAA Aviation 2019 Forum

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“…I n recent years, structured overset grid technology has been successfully applied to computational fluid dynamics analysis on a wide variety of complex aerospace applications. [1][2][3][4][5][6][7][8][9][10][11] While structured overset grid flow solvers such as OVERFLOW 12 and LAVA 13 are highly e cient relative to typical flow solvers utilizing unstructured grids, structured overset grid generation remains a labor intensive and time consuming step relative to unstructured methods. Grid generation for overset structured grids usually consists of three steps: surface grid generation, volume grid generation, and domain connectivity.…”

Section: Introductionmentioning

confidence: 99%

Strategies Toward Automation of Overset Structured Surface Grid Generation

Chan

2017

23rd AIAA Computational Fluid Dynamics Conference

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An outline of a strategy for automation of overset structured surface grid generation on complex geometries is described. The starting point of the process consists of an unstructured surface triangulation representation of the geometry derived from a native CAD, STEP, or IGES definition, and a set of discretized surface curves that captures all geometric features of interest. The procedure for surface grid generation is decomposed into an algebraic meshing step, a hyperbolic meshing step, and a gap-filling step. This paper will focus primarily on the high-level plan with details on the algebraic step. The algorithmic procedure for the algebraic step involves analyzing the topology of the network of surface curves, distributing grid points appropriately on these curves, identifying domains bounded by four curves that can be meshed algebraically, concatenating the resulting grids into fewer patches, and extending appropriate boundaries of the concatenated grids to provide proper overlap. Results are presented for grids created on various aerospace vehicle components.

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Wedge Shock and Nozzle Exhaust Plume Interaction in a Supersonic Jet Flow

Castner

Zaman

Fagan

et al. 2017

Journal of Aircraft

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Fundamental research for sonic boom reduction is needed to quantify the interaction of shock waves generated from the aircraft wing or tail surfaces with the nozzle exhaust plume. Aft body shock waves that interact with the exhaust plume contribute to the near-field pressure signature of a vehicle. The plume and shock interaction was studied using computational fluid dynamics and compared with experimental data from a coaxial convergent-divergent nozzle flow in an open jet facility. A simple diamond-shaped wedge was used to generate the shock in the outer flow to study its impact on the inner jet flow. Results show that the compression from the wedge deflects the nozzle plume and shocks form on the opposite plume boundary. The sonic boom pressure signature of the nozzle exhaust plume was modified by the presence of the wedge. Both the experimental results and computational predictions show changes in plume deflection.

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Numerical Simulations of Shock/Plume Interaction Using Structured Overset Grids

Cited by 10 publications

References 16 publications

Efficient Near-Field to Mid-Field Sonic Boom Propagation Using a High-Order Space Marching Method

Efficient Near-Field to Mid-Field Sonic Boom Propagation Using a High-Order Space Marching Method

Strategies Toward Automation of Overset Structured Surface Grid Generation

Wedge Shock and Nozzle Exhaust Plume Interaction in a Supersonic Jet Flow

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