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- W2099681244 abstract "An Eulerian‐Lagrangian two-phase approach suitable for the numerical simulation of the multiphase reacting internal e ow in a solid rocket motor with a metalized propellant is discussed. An Eulerian description has been used to analyze the motion of the continuous phase that includes the gas as well as the small (micrometer-sized ) particulates, whilea Lagrangian description is used for the analysis of the discrete phase that consists of the larger particulates in the motor chamber. An empirical model is used to compute the combustion rate for agglomerates, whereasthecontinuous-phasechemistry istreatedusingchemicalequilibrium.Acomputercodeincorporating this analysiswasusedtosimulatethereactinge owinasolidrocketmotorwithanammoniumperchlorate (AP)/hydroxyl terminatedpolybutadiene (HTPB)/aluminum(Al)propellant.Thecomputedresultsindicatethattherelativelyslow combustion rate of aluminum droplets can result in an extended combustion zone in the chamber rather than a thin reaction region. Thepresenceof the extended combustion zone resultsin thechamber e owe eld being far from isothermal and the chemical composition being far from uniform, as would be predicted by a surface combustion assumption.Thetemperatureinthechamberincreasesfromabout2600Katthepropellantsurfacetoabout3550 K inthecore. Similarly thechemicalcomposition andthedensity ofthepropellantgasalso showspatiallynonuniform distribution in the chamber. The analysis discussed provides a moresophisticated toolfor solid rocket internal e ow predictions than is presently availableand can beuseful in studying apparent anomalies and improving the simple correlations currently in use." @default.
- W2099681244 created "2016-06-24" @default.
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- W2099681244 date "2003-01-01" @default.
- W2099681244 modified "2023-10-01" @default.
- W2099681244 title "Numerical Simulation of Distributed Combustion in Solid Rocket Motors with Metalized Propellant" @default.
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- W2099681244 doi "https://doi.org/10.2514/2.6101" @default.
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