Numerical simulation on the 3-D flow-field of solid-rocket-motor combustion chamber

The laminar Navier-Stokes equations and the SIMPLE algorithm were used here to solve the three-dimensional flow-field in the combustor of solid-propellant rocket-motor with a movable boundary (owing to the burning-out of solid propellant). The stagger-grid technique was adapted, and in the flow-field calculation, the mesh division is not conducted, only the values on the points of grid are read out directly. In this way the problem of insufficient memory in the present computer was solved, and satisfactory results were obtained.