摘要
本文应用最小喷管长度理论对二维超燃冲压发动机尾喷管上壁型线进行了设计,并对尾喷管性能进行了计算,应用粒子群优化算法对所设计的喷管型线进行了优化。为超燃冲压发动机尾喷管几何参数的选择提供了参考范围。
In this thesis, the scramjet nozzle has been designed by the least nozzle length theory. The nozzle characteristic has been calculated. The nozzle line has been optimized by particle swarm optimization method. The research conclusions provide instruction for the choice of geometric parameters in the nozzle design.
出处
《长春理工大学学报（自然科学版）》
2007年第1期113-116,共4页
Journal of Changchun University of Science and Technology(Natural Science Edition)
基金
航天基础科学基金(01c53020)
