Recently, the hybrid rocket propulsion has become attractive to the research community and has developed the trend to become an alternative to the conventional liquid and solid rockets. The hybrid rocket is a combination of both the solid and liquid
systems with half of the plumbing of the liquid rocket but retaining the flexibility of operation and avoiding the explosive nature of the solid rocket.Among available hybrid systems, the N2O-HTPB hybrid propulsion represents the simplest but
sufficiently efficient design. Unfortunately, even until now, research in developing hybrid N2OHTPB propulsion system still strongly depends on trials-and-errors, which are time-consuming and expensive. Thus, detailed understanding of the
fundamental combustion processes that are
involved in the N2O-HTPB propulsion system can greatly impact the research community in this field.This may further facilitate the successful modeling of the combustion processes and help improving the design of N2O-HTPB propulsion system in the future. A comprehensive numerical model with real-fluid properties and finite-rate chemistry is
developed in this research to predict the combustion flowfield inside a N2O-HTPB hybrid rocket system.Good numerical predictions as compared to experimental data are also presented.