고체 로케트 모타내의 비압축성Navier-Stokes해석

The steady-state, incompressible, laminar flow inside a solid prepellant rocket motor is numerically simulated by solving the three-dimensional, incompressivel Navier-Stokes equations in curvilinear coordinates with a pseudocompressibility approach. By introducing a time derivative of pressure into the continuity equation, the steady-state incompressible Navier-Stokes equations are solved in an efficient manner by means of an implicit algorithm. The multi-block method is employed to handle geometric complexity due to the cross sectional configuration of star-shaped propellant grain. For the analysis, the propellant burning surface of rocket motor is assumed to be fixed and modeled as an injecting boundary through which burned gases are ejected. Computational results are to be applied to fix the cross sectional shape of propellant grain of rocket motor.