摘要
首先对矩形截面高超声速进气道设计方法进行了研究,给出了设计流程,并据此设计了矩形截面高超声速进气道。接着对其进行了三维数值仿真研究,给出了进气道性能参数随来流马赫数、飞行迎角及飞行高度的变化规律。最后设计了实验模型,并进行了高焓风洞实验验证。数值模拟及高焓风洞实验验证均表明:本文采用的设计方法可达到预期的设计效果,设计的进气道达到了相应的设计要求;本文采用的数值仿真方法可以较为准确地模拟高超声速进气道内的流动,数值模拟结果可信。
The design method for a hypersonic inlet with a rectangular section is presented and the inlet is designed at the point of Ma = 6.0. The flow in the hypersonic inlet is analyzed with a three-dimensional numerical analyzer. The flow characteristics at different Mach numbers, attack angles and flying attitudes are also discussed. The preliminary test verification is conducted in the hypersonic inlet at Ma = 6 in a high enthalpy tunnel. The total pressure and static pressure distributions in flow of the inlet are obtained and compared with the calculation data. The result shows that the numerical results have basic flow characteristics. Both the numerical simulation and the experimental result show that the design method is feasible for the hypersonic inlet with the rectangular section.
出处
《南京航空航天大学学报》
EI
CAS
CSCD
北大核心
2009年第4期423-428,共6页
Journal of Nanjing University of Aeronautics & Astronautics
基金
国家高技术发展研究计划("八六三计划")资助项目
关键词
高超声速进气道
设计方法
矩形截面
实验验证
hypersonic inlet design method
rectangular section experimental verification