Computation of two-phase viscous flow in solid rocket motors using aflux-split Eulerian-Lagrangian technique

Numerical Simulation of Gas-Particle Two-Phase Flow in a Nozzle with DG Method

“…CJ Hwang and GC Chang [4] computed the gas-particle two-phase flow in a nozzle by using time-dependent explicit MacCormark scheme to solve the gas equations and tracking the particle trajectories with Lagrangian approach. Golafshani and Loh [5] also used particle-trajectory model to compute the mixed flow of viscous gas and particles in a JPL nozzle and estimated the deposition of particulate debris in the shuttle engine based on the computation results. Madabhushi et al [6] studied the Aft-Dome two-phase flow field in solid rocket motor with submerged nozzle and a turbulence model was included into 2 Discrete Dynamics in Nature and Society the computation.…”

Convective Heat Transfer in the Reusable Solid Rocket Motor of the Space Transportation System

“…This analysis was performed to maintain a continuity with previous analyses [3][4][5][6][7][8] of this motor; serve as a non-vectored baseline for any three-dimensional vectored nozzles; provide a relatively simple application and test for various CFD solution schemes, grid sensitivity studies, and turbulence heat transfer/modeling; and calculate the nozzle convective heat transfer coefficients. The purpose of this study was to determine the convective heat transfer in the RSRM.…”

“…First, Golafshani and Loh [3] conducted a two-dimensional, axisymmetric numerical solution of the Navier-Stokes equations to analyze the viscous coupled gas-particle non-reacting flow in solid R. A. AHMAD rocket motors. The solution assumed laminar internal flow.…”

Plume Flow Field Analysis of Solid Rocket Motor

“…Under angle of attack, the pure gas effect and gas-solid two-phase flow the effect, numerical simulation using FLUENT software. Based on two dimensional axisymmetric model , N-S equation and turbulence model [1,2,3] , the plume flow field of solid rocket motor is compared with different flight altitude and flight Maher number under the condition of constant attack angle.…”