Abstract: A model based on numerical solution of Navier Stokes equations was established for two dimensional scramjet nozzle optimization design. The optimum solution subjected to different constrains was obtained with Complex Optimization Method. Nozzle performances was improved after optimization. The effects of flight Mach number and cowl length on scramjet nozzle performances was evaluated, respectively. The results are useful for further design of scramjet nozzles.

Key words: Hypersonic ramjet engine;Supersonic combustion;Engine nozzle;Optimization design;Numerical simulation

摘要： 为得到二维超声速燃烧冲压发动机尾喷管最优型面,建立了二维尾喷管基于N S方程的优化设计模型,运用复合形优化方法对该模型进行求解,得到了尾喷管型面的优化设计,结果表明,尾喷管性能参数有明显的提高,推力系数和升力系数升高,俯仰力矩系数降低;同时,随着飞行马赫数的降低,推力系数和俯仰力矩系数都会下降,而升力系数却上升。并且初步研究了尾喷管下壁长度对尾喷管性能的影响,为超燃冲压发动机尾喷管设计提供一定参考。

关键词: 高超音速冲压发动机;超音速燃烧;发动机喷管;最优设计;数值仿真