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The simulation of solid propellant rocket exhaust plumes using 3D Navier-Stokes codes requires substantive computer resources to account for both chemical and particulate nonequilibrium effects. Particulate nonequilibrium effects are dealt with by solving a system of particulate (dispersed-phase) equations that (under dilute volumetric approximations) interact via source terms representing interphase drag and heat transfer.
Two particulate solution methodologies are available, namely:
(1) Eulerian continuum-cloud solution methodology whereby the particle size distribution is subdivided into bins and a system of continuum-like equations is solved for each size bin; and,
(2) Lagrangian particle tracking solution methodology whereby each particle (or an ensemble of N particles) is discretely analyzed and statistics are gathered to permit evaluating the interphase source terms.
Eulerian methodology is computationally more efficient but has limitations in its ability to represent particle physics in complex flows (e.g. particles of a given type/size can only have one set of properties at a point which precludes treating crossing streams, wall reflections, etc.).
Lagrangian methodology can deal with the particle physics of complex flows but requires special procedures to minimize the statistical sampling size and to ensure spatial accuracy.
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| Multi-Phase Flow Research: |
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• Particulate Flows |
