Hybrid, viscous, unstructured mesh solver for propulsive applications

Hosangadi, Ashvin; Lee, R.; Cavallo, Peter A.; Sinha, Neeraj; York, B. J.

doi:10.2514/6.1998-3153

Cited by 62 publications

(24 citation statements)

References 9 publications

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“…The case considered for this is supersonic flow over a ramp at an approach Mach number of 3.0. This is a standard test case and we compare the solution of the multiphase CRUNCH code with that obtained from the standalone compressible CRUNCH code [39,40]. The comparisons are shown in Figure 6.9, where pressure contours are plotted from both solutions.…”

Section: Single Phase Compressible Validation -Supersonic Rampmentioning

confidence: 99%

“…This procedure leads to savings in computational resources, since the interface is first identified and then the grid in the vicinity of the interface is refined. In work described below, we present a generalized mixture formulation model that extends the framework of our CRUNCH compressible unstructured code [39,40] to include varied elements required for the liquid breakup problem. We describe this in progressive steps.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

CFD of Complex Three-Dimensional Multiphase Flowfields

Perrell¹,

Tonello²,

Hosangadl³

et al. 2002

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Section: Single Phase Compressible Validation -Supersonic Rampmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

CFD of Complex Three-Dimensional Multiphase Flowfields

Perrell¹,

Tonello²,

Hosangadl³

et al. 2002

Self Cite

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“…The reader is referred to Ref. 8 for more details on the combustion modeling approach implemented in CRUNCH CFD ® . The inviscid flux procedure involves looping over the edge list and computing the flux at the dual face area bisecting the edge.…”

Section: Numerical Framework For Flame Deflector Spray Nozzlesmentioning

confidence: 99%

“…CRUNCH CFD ® Numerical Framework The CRUNCH CFD ® code is a multi-element (i.e. tetrahedral, prismatic, pyramid, and hexahedral cells) unstructured flow solver for viscous, real gas systems [7][8][9] . It is formulated for an edge-based data framework where the solution is saved at the cell-vertex and a dual control-volume is defined by cutting across all edges coming to a node.…”

Section: Numerical Framework For Flame Deflector Spray Nozzlesmentioning

confidence: 99%

Analysis of Flame Deflector Spray Nozzles in Rocket Engine Test Stands

Sachdev¹,

Ahuja²,

Hosangadi³

et al. 2010

46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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The development of a unified tightly coupled multi-phase computational framework is described for the analysis and design of cooling spray nozzle configurations on the flame deflector in rocket engine test stands. An Eulerian formulation is used to model the disperse phase and is coupled to the gas-phase equations through momentum and heat transfer as well as phase change. The phase change formulation is modeled according to a modified form of the Hertz-Knudsen equation. Various simple test cases are presented to verify the validity of the numerical framework. The ability of the methodology to accurately predict the temperature load on the flame deflector is demonstrated though application to an actual sub-scale test facility. The CFD simulation was able to reproduce the result of the test-firing, showing that the spray nozzle configuration provided insufficient amount of cooling.

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“…An edge-based data structure is employed wherein a polyhedral control volume is constructed from the union of all cells incident to a given node, and the control volume faces are associated with each edge. The inviscid flux calculation proceeds by looping over all edges in the mesh, and is grid-transparent, while a cell-based method is employed to compute the flowfield gradients at the control volume faces for evaluating the viscous fluxes [8]. Turbulence modeling is provided by a k-ε model with various near-wall, compressibility, and EASM extensions.…”

Section: Performing Organization Name(s) and Address(es)mentioning

confidence: 99%

Parallel Unstructured Mesh Adaptation for Transient Moving Body and Aeropropulsive Applications

Cavallo

Sinha

Feldman

2004

42nd AIAA Aerospace Sciences Meeting and Exhibit

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*Adaptive, unstructured grid methods, in which the mesh is allowed to deform, and grid quality subsequently restored through localized coarsening and refinement, offer the potential of a more rapid, straightforward approach to generalized moving body problems. Automation of this mesh movement and quality correction strategy requires a close coupling with the flow solution process. With parallel simulations now common, parallel coarsening and refinement methods for moving meshes are needed. In this work, parallel mesh adaptation strategies are developed to treat deforming, decomposed domains. Distortion of the moving mesh is assessed using a deformation matrix analysis. A two-pass approach is implemented in which cell migration shifts the interprocessor boundary, thereby accommodating coarsening and refinement of the interprocessor faces. The adapted grids are rebalanced among the processors using available techniques. Representative cases are presented to demonstrate the parallel approach and maintenance of cell quality for practical separation events.

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Hybrid, viscous, unstructured mesh solver for propulsive applications

Cited by 62 publications

References 9 publications

CFD of Complex Three-Dimensional Multiphase Flowfields

CFD of Complex Three-Dimensional Multiphase Flowfields

Analysis of Flame Deflector Spray Nozzles in Rocket Engine Test Stands

Parallel Unstructured Mesh Adaptation for Transient Moving Body and Aeropropulsive Applications

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