INTERNATIONAL JOURNAL OF RESEARCH AND INNOVATION IN ENGINEERING TECHNOLOGY
Abstract
The usage of ramjet engine is very important in the missile and aircraft propulsion. When it is cruising at supersonic air velocity the flow characteristic of the ramjet engine produces a shock wave. This formation of shock wave will raise the pressure of the upstream airflow in front of the inlet cone. This pressure rise with reduced air speed is suitable for the subsonic combustion of the ramjet engine. The cone will help to change the area of the ramjet engine inlet and mass flow rate of the incoming pressure raised air. The change in mass flow rate of the inlet leads to the variation in thrust production. This engine is integrated with a convergent-divergent nozzle to produce supersonic velocity at the nozzle exit. This variation in thrust production is to be studied in detail. In this project, the variable inlet area ramjet engine design and model is investigated. In order to predict the thrust value for variable inlet area ramjet engine by using commercial numerical codes. The increment of thrust value will be expected by using the variable inlet area ramjet engine, which means it attains more thrust
