Numerical Simulations of Combustive Flows in a Swirling-Oxidizer-Flow-Type Hybrid Rocket

Abstract

The objective of this study is to clarify inner state of a chamber of the Swirling-OxidizerFlow-Type Hybrid Rocket which is one of the types of a Hybrid Rocket by means of numerical fluid analysis. In this study, a numerical code which uses the Large Eddy Simulation as a turbulent modeling and the Flamelet approach as combustion modeling is constructed, and the code is applied to the analysis of the swirling chamber. On this occasion, in order to guarantee an applicability of the results, an experiment of the diffusion flame swirling burner is simulated by the code, and it is confirmed that results of the simulation are well corresponding qualitatively and partially quantitatively to experimental data. Then, a simulation for the chamber of the Swirling-Oxidizer-Flow-Type Hybrid Rocket is done by the numerical code, and it can be obtained that the numerical results are well corresponds qualitatively to visualized data of the experiment. Due to the analysis using this numerical code, structure of flow and flame, distributions of physical quantities and chemical species and state of turbulent eddies are clarified in the chamber of the hybrid rocket.