Modeling and Analysis of a Rocket Based Combined Cycle Rocket Nozzle

Abstract

This project develops a rocket nozzle. The nozzle is designed in such a way that the divergent portion of the nozzle geometry must pass through a clover that is placed on the perimeter, thus creating a space for air intake into the centre of an annular rocket exhaust stream. The main objective of this project is to determine the best one from (3clover, 4clover and 5 clovers) and comparison of numerical simulation to a predefined Mach number distribution of in viscid solution and viscous simulation using the k- model will be attempted. Geometry designs and Meshing were made in ICEM CFD 13.0 and an analysis is carried out in FLUENT 13.0. Based on the flow analysis it is found that nozzle with 4 clovers/gates provides better results when compared with the other i.e., 3 or 5 clovers/gates and it is one of the suggested and effective design of the nozzle. In viscid area-averaged computational results are within 2.1% of the predefined outlet Mach number of 2.75 and 7.6% of the isentropic pressure predicted at the outlet. Viscous computational results obtained using the k-e turbulence model under-predict the predefined outlet Mach number by 4% which is acceptable.