与进气道相容的飞行器乘波-楔形前体气动特性及重构研究

项目名称： 与进气道相容的飞行器乘波-楔形前体气动特性及重构研究

项目编号： No.51206077

项目类型： 青年科学基金项目

立项/批准年度： 2013

项目学科： 工程热物理与能源利用学科

项目作者： 袁化成

作者单位： 南京航空航天大学

项目金额： 25万元

中文摘要： 飞行器进气道/前体的一体化设计是实现高超声速飞行的关键。本项目拟将乘波体气动性能优势与升力体结构特征优势相结合，对一种兼顾乘波体气动特性和升力体结构特征、与进气道相容的高超声速飞行器乘波-楔形前体设计方法开展研究。通过数值模拟细致刻画其三维波系结构及流动特征，凝炼影响气动性能的几何描述参数，分析和揭示其耦合流动机理。并据此开展此类前体/进气道流场的气动重构原则与方法研究。最终获得综合考虑前体升阻力特性、有效容积及进气道内流性能的乘波-楔形前体/进气道一体化气动布局方案。在此基础上，针对设计和非设计工况，对此一体化布局方案开展三维数值模拟分析与风洞试验研究，验证并掌握此类一体化构型的总体性能、流动特征与工作特性，为我国近空间飞行器相关技术的研究提供技术储备。

中文关键词： 高超声速；乘波前体；进气道；耦合设计；楔形前体

英文摘要： The integration of hypersonic vehicle forebody and inlet is very important to achieve hypersonic flying. Based on the waverider and liftbody concept, a coupling design method of the hypersonic waverider - wedge-shaped forebody that with flow patterns of waverider and configuration characteristics of liftbody is researched, the forebody and hypersonic inlet with rectangular section integration design is done also. The shock wave structure and coupling flow characteristics of hypersonic waverider - wedge-shaped forebody and inlet with rectangular section was analyzed with three-dimensional numerical analyzer. The geometry parameter which affects flow characteristics of forebody and inlet is investigated. The coupling design principle and method of hypersonic waverider - wedge-shaped forebody and inlet with rectangular section is presented. An integration of hypersonic forebody/inlet case is designed, the performance and flow characteristics of forebody/inlet at different inflow Mach number is presented with three-dimensional numerical analyzer. The preliminary test verification would conducted on the hypersonic waverider - wedge-shaped forebody with inlet in a hypersonic tunnel.

英文关键词： hypersonic；forebody waverider；inlet；coupling design；wedge-shaped forebody