The main objective is to analyze a rocket
engine nozzle to understand the phenomena of various design conditions under
different convergent angle, divergent angle and throat radius by Computational
Fluid Dynamic (CFD). There have also mentioned about inlet boundary conditions
with specification according to the experimental information. The paper also
addresses static pressure optimization and Mach number optimization. The values
on the basis of results along by optimal values of nozzle design parameters
obtained from optimization techniques of Taguchi Design. Convergent angle,
Divergent angle and Throat radius are considered. Also response of static
pressure and Mach number values of CFD analysis in two types of inlet pressure
value applied for optimal parameters of nozzle attained.
