A Review on Supersonic Nozzle Design and Analysis with Traditional Methods

The optimization of rocket nozzle design remains critical for advancing the efficiency and performance of space propulsion systems. This investigation presents an in-depth analysis of supersonic nozzle configurations and their aerodynamic behaviors, with a specific focus on methodologies to design a contour capable of enhancing thrust by reducing losses under. Further concepts of compressible aerodynamics and CFD are also reported, compassing the state of the art in chapters 1 and 2 necessary to base the studies reported. Chapter 3 investigates traditional nozzle designs, specifically conical and bell nozzles, employing the Method of Characteristics (MOC) to compute their flow characteristics and optimize geometrical parameters for minimum length and maximum thrust efficiency. Various design contours, including parabolic and truncated ideal configurations, are evaluated for their applicability in diverse applications such as supersonic wind tunnels and propulsion systems.In Chapter 4, the research extends to advanced nozzle geometries, including aerospike, dual-bell, expansion-deflection, and multi-grid nozzles, each offering unique advantages in adapting to varying pressure environments. These designs are analyzed for their ability to mitigate under- and over-expansion losses, improved thrust coefficient, and enhance specific impulse. The studies emphasize the critical balance between design complexity, manufacturing constraints, and aerodynamic performance, establishing guidelines for integrating innovative design features into modern propulsion systems.Computational simulations and theoretical formulations underscore the effectiveness of improved MOC techniques and boundary-layer corrections in accurately predicting nozzle performance. The findings have broad implications for the development of propulsion systems in high-demand applications, including single-stage-to-orbit (SSTO) vehicles and hypersonic flight systems.