Design and simulation of supersonic inlet performance with combustion chamber based on specific ramjet requirements

Inlet in ramjet engines are used to reduce the air flow from free stream to the required speed for flame stability in the combustion chamber. Hence the precise and correct design of inlet have rightly influence on whole system of ramjet engine performance. At the present work, an axisymmetric supersonic inlet with external compression has been designed based on requirements of the ramjet engine at Mach 2.1. Steady flow simulation was done for inlet individually by CFD software in different fuel flow and Mach numbers to investigate the inlet performance that integrated by other parts of engine. Then transient simulation performed for integrated engine by selection of a special fuel flow-time function that injected in combustor. The results of simulation exhibited the shock velocity and performance of inlet that integrated by the engine. The results show that the designed geometry can meet the desired performance requirements considering the fuel control system ability.