Computational Analysis of Nozzle Configurations
for Performance Enhancement in Missile Propulsion
Systems
Objective
This study aims to analyse the aerodynamic performance of different
nozzle configurations for missile applications using Computational
Fluid Dynamics (CFD). Various nozzle geometries, including
convergent-divergent (C-D), bell-shaped, and conical designs, are
simulated under a given operating condition to evaluate their impact on
thrust, specific impulse, and shockwave behaviour. The objective is to
identify an optimal nozzle configuration or to compare the difference in
performance parameters.
Problem Statement
The efficiency and performance of a missile propulsion system is
highly dependent on the operating parameters such as missile
weight (Propellant & Structure), Nozzle configuration etc.
Comparative performance analysis of various nozzle
configurations to identify the design which produces the
maximum thrust with higher specific impulse.
Novelty
Unlike conventional studies that focus on a single nozzle design, this
research systematically compares multiple nozzle geometries,
including C-D, bell-shaped & conical designs, under specific operating
condition using CFD. The novelty of this work lies in evaluating nozzle
