Reacting flow simulations represent a formidable challenge in numerical analysis because they incorporate complex mechanisms from various reacting flows alongside high-velocity fluid dynamics. This intersection makes them among the most intricate types of computational analyses available. A comprehensive review of existing experimental models, critical input parameters, and the methodologies behind active simulation methods is essential for advancing the field. This review emphasizes the fundamental processes that consistently affect the accuracy and predicted flow properties of a hybrid-rocket combustion model. It discusses various turbulence models, chemical mechanisms, and dimensional analyses. The key features of these turbulence, chemistry and dimensional models are outlined, and it was found that the existing numerical models have limited applicability to a complete hybrid rocket engine configuration. The review identifies the lacuna in the numerical and experimental models of hybrid rocket engines. The study also surveys current and planned space missions that use hybrid propulsion, thereby providing market context. Additionally, the paper explores solutions to common errors, offering insights on how to avoid them to minimize inaccuracies and instabilities in simulations. It summarises crucial overlooked aspects and proposes steps to address these issues comprehensively. The research also proposes a method for evolving the numerical model of hybrid rocket engines so as to reduce computational cost and time.
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Pallela et al. (2026) studied this question.