COMPUTATION OF TURBULENT REACTING FLOW IN A SOLID-PROPELLANT DUCTED ROCKET

A mathematical model for computation of turbulent reacting flows is developed under general curvilinear coordinate systems. An adaptive, streamline grid system is generated to deal with the complex: flow structures in a multiple-inlet solid-propellant ducted rocket (SDR) combustor, General tenser representations of the k-epsilon and algebraic stress (ASM) turbulence models are derived in terms of contravariant velocity components, and modification caused by the effects of compressible turbulence is also included in the modeling. The clipped Gaussian probability density function is incorporated in the combustion model to account for fluctuations of properties, Validation of the above modeling is first examined by studying mixing and reacting characteristics in a confined coaxial-jet problem, This is followed by study of nonreacting and reacting SDR combustor flows. The results show that Gibson and Launder's ASM incorporated with Sarkar's modification for compressible turbulence effects based on the general curvilinear coordinate systems yields the most satisfactory prediction for this complicated SDR flowfield.