Convergent-divergent nozzles(CDN), commonly used in rocket engines, jet
propulsion, and industrial gas turbines, are essential for accelerating fluid flow to
supersonic speeds. This review explores the optimization and performance analysis of
these nozzles, focusing on factors such as nozzle geometry, pressure ratios, and
boundary conditions. Optimizing these parameters enhances nozzle efficiency,
reduces energy losses, and ensures stable supersonic flow. Geometric optimization
involves refining the nozzle's contour to reduce flow separation and minimize
shockwave formation, particularly in the divergent section. Additionally, achieving an
optimal pressure ratio between the inlet and outlet plays a significant role in
maximizing exhaust velocity and minimizing shock-induced losses. Performance
analysis is conducted through computational fluid dynamics (CFD). Simulations are
used to predict flow characteristics, Mach number distributions, and shock locations,
while experimental tests validate these models by measuring parameters such as thrust,
exhaust velocity, and specific impulse. By combining these techniques, the study
provides comprehensive insights into the behavior of convergent-divergent nozzles
under various operating conditions. The results contribute to the design of more
efficient propulsion systems, emphasizing the importance of nozzle optimization in
enhancing the performance of aerospace and industrial applications involving high-
speed fluid flow.