A supersonic inlet plays a predominant role in obtaining the optimal thrust in a ramjet engine. Since there are no moving parts in a ramjet, the air gets compressed by the formation of a series of oblique and normal shock along the inlet to ensure that combustion occurs at subsonic flow. Generation thrust is depends on the inlet aerodynamic design, so there is a need for an optimal design for the maximum efficiency. In this work, design of optimal inlet design is carried out using the meta-heuristic optimization scheme. Initially, the Bezier curve parameterization method and QuickerSim flow analysis tool are coupled with genetic algorithms to parametrize the inlet design and to identify the total pressure recovery over an inlet respectively. The objective function of optimization scheme is to design the optimal inlet design by maximizing the total pressure recovery under a constraint. The complete cycle is coded in Matlab platform to reduce the computational cost.
展开▼
