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.

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Ms. BILLA PALLAVI