Abstract Modeling and simulation of the motion of agglomerates with a complex composition and shape in the flow of combustion products is of interest for problems related to design and optimization of solid propellant rocket motors. An approach is developed for modeling of unsteady processes that occur when a particle consisting of an aluminum droplet and a condensed oxide particle attached to it (aluminum droplet with oxide cap) is transported by a viscous incompressible fluid flow. Methods are proposed to take into account the sliding of an attached oxide particle over the surface of the aluminum droplet. The results of numerical computations are used to find the drag and heat transfer coefficients of a non-spherical particle at flow velocities corresponding to the formation of separation zones. The constructed model is one of the components of a more general mathematical model designed to calculate two-phase flows of combustion products based on a multi-scale approach to the simulation of two-phase flows in a complex environment.

    Highlights Simulation of various flowfields around non-spherical particle is performed. Various flow regimes around aluminum droplet with oxide cap are identified. Computational results are compared with experimental and literature data. Flow regimes are compared with those for rigid sphere.


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    Titel :

    Drag and heat transfer of metal and oxide agglomerates in flow of combustion products of solid propellant


    Beteiligte:

    Erschienen in:

    Acta Astronautica ; 205 ; 319-331


    Erscheinungsdatum :

    2022-09-11


    Format / Umfang :

    13 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch