二维高超声速进气道优化设计方法研究  

Study of Optimization Method for Two-Dimensional Hypersonic Inlet

作　　者：王向转[1] 詹浩[1] 朱军[1] 

机构地区：[1]西北工业大学航空学院,陕西西安710072

出　　处：《飞行力学》2009年第4期25-27,31,共4页Flight Dynamics

摘　　要：对二维高超声速进气道的优化设计方法进行了研究。采用拟Newton法作为优化方法,结合代数法生成的结构化网格以及流体计算软件Fluent,形成对二维高超声速进气道进行二维优化设计的设计软件系统。运用该系统,以总压恢复系数为目标,分别对3道激波外压、1道激波内压和3道激波外压、2道激波内压的二维高超声速进气道在设计点(飞行马赫数6.0,飞行高度25 km)进行了二维优化设计。设计算例表明,运用该系统对二维高超声速进气道进行优化设计是切实可行的。The optimization and design methods for the two-dimensional hypersonic inlet are done in this paper. The quasi-Newton method, structured grid and using Fluent software are combined to form a system to optimize and design the two-dimensional hypersonic inlet. By using this system to attain the general pressure recovering parameter, under the design point（flight Mach number is 6 and altitude is 25 km） ,the hypersonic inlet with 3 external shock compression ramps and 1 internal shock compression ramp, the hypersonic inlet with 3 external shock compression ramps and 2 internal shock compression ramps are optimized and designed. The design results are satisfied. The design example proves that the method and the software developed by this thesis have a significant practical value for optimization of a two-dimensional hypersonic inlet.

关 键 词：高超声速进气道 二维优化设计 拟NEWTON法 

分 类 号：V221[航空宇航科学与技术—飞行器设计]