Numerical Simulation of Solid Propellant Rocket Exhaust Plume Considering Two-Phase Flow Effects

Yan Jie Ma; Fu Ting Bao; Hao Xu; Lin Sun

doi:10.4028/www.scientific.net/AMM.798.185

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HomeApplied Mechanics and MaterialsApplied Mechanics and Materials Vol. 798Numerical Simulation of Solid Propellant Rocket...

Numerical Simulation of Solid Propellant Rocket Exhaust Plume Considering Two-Phase Flow Effects

Abstract:

Two-phase flow can have significance influence on exhaust plume of solid propellant, as well as the infrared radiation of the rocket. To show this influence, flow field of solid propellant rocket exhaust plume is simulated on different working conditions, where two-phase flow is involved using the DPM method. Comparing the flow filed results with or without two-phase flow considered shows that the existence of the condensed particles can decreases the velocity of the plume and increases the temperature. The influences of the flight height and Mach number on exhaust plume are also discussed.

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Periodical:

Applied Mechanics and Materials (Volume 798)

Pages:

185-189

DOI:

https://doi.org/10.4028/www.scientific.net/AMM.798.185

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Online since:

October 2015

Authors:

Yan Jie Ma*, Fu Ting Bao, Hao Xu, Lin Sun

Keywords:

Numerical Simulation, Plume, Solid Propellant Rocket, Two-Phase Flow

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* - Corresponding Author

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