Flow Field and Heat Transfer Characteristics of an Axisymmetric Air Augmented Rocket

Abstract

An axisymmetric air augmented rocket (AAR) has been studied to test mixing chamber at the static pressure and mass flow rate at the outlet which provided thrust to the rocket. The entrainment ratio is affected due to secondary flow (Low mass flow rate) at inlet induced by primary flow (High mass flow rate). This paper gives details of the computational simulation of flow field as well as heat transfer phenomena inside the mixing chamber of an ejector. The fluent 15.0 has been chosen for the simulation of the supersonic flow along with shock wave creation inside the air to air ejector on the basis of the computational fluid dynamic (CFD) method. In this computational process, a finite volume scheme and density-based solver have been applied for a better result. The SST k − ω turbulent model with implicit formulation has been used considering the accuracy and the stability. The geometry has been changed for the purpose of the improvement of the mass flow rate of discharge. The whole process is validated by the data from the experimental available in the literature on the basis of static pressure distribution. The results show the situation inside the mixing chamber for different-different operating conditions of primary, secondary and discharge pressure.