| The scramjet is a new type of air-breathing propulsion device, which has remarkable performance, great potential superiority, and has a good prospect in the field of aeronautics and astronautics in the future. The scramjet is composed of inlet, isolator, combustor and nozzle. Nozzle is an important component of the scramjet, which produce thrust. The nozzle performance is related with geometric parameters, free-stream Mach number, flight dynamic pressure, attack angle and the performance of inlet and combustor. The nozzle design and the influence of geometric parameters on the nozzle performance are emphasized by researchers in the world for decades.In this thesis, the scramjet nozzle has been designed and optimized by the method of characteristic line. The internal flow field of nozzle is simulated by FLUENT. The influence of geometric parameters (expending angle, total length, total height, the length of cowl and cowl angle) on the nozzle performance is studied. The design and optimization of the nozzle is researched by use of the method of characteristic line and particle swarm optimization method.The research results show that the method of characteristic line is feasible for the nozzle design. The research conclusions provide instruction for the choice of geometric parameters in the nozzle design. |
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