高超声速进气道不起动流场大尺度分离流动的实验研究

项目名称： 高超声速进气道不起动流场大尺度分离流动的实验研究

项目编号： No.11502294

项目类型： 青年科学基金项目

立项/批准年度： 2016

项目学科： 数理科学和化学

项目作者： 赵一龙

作者单位： 中国人民解放军国防科技大学

项目金额： 20万元

中文摘要： 高超声速进气道起动与否是关系超燃冲压发动机能否正常工作乃至整个高超声速飞行成败的关键因素之一。高超声速进气道不起动流场结构复杂，且起动与不起动过程中流场变化迅速，研究难度较大。进气道不起动流场最显著的标志在于内收缩段入口处存在大尺度分离流动，本项目拟在前期工作的基础上对高超声速进气道不起动大尺度分离流动开展实验研究。通过实验的方法获取大尺度分离流动的精细流场结构及非定常特性，并结合理论分析建立相应的大尺度分离流动模型。借助于变Ma数风洞等实验设备，研究来流变Ma数、变收缩比以及反压作用下不起动大尺度分离流动的形成及消失机制。项目研究将加深对高超声速进气道不起动大尺度分离流动的认识，揭示进气道起动/不起动的流动机理，为提升进气道的起动性能以及改进进气道设计方法等提供参考。

中文关键词： 高超声速；进气道；不起动；大尺度；分离

英文摘要： The start of hypersonic inlet is a guarantee for the normal work of the scramjet and the hypersonic vehicle. The flowfield in the hypersonic inlet is very complicated and the transformation between the start and unstart is prompt, which make the research difficult. The marked characteristic of the inlet unstarted flowfield is the large-scale separation located in the entrance of the inner-contraction of the inlet. The large-scale separation in the unstarted flowfield will be researched by experiment based on the prophase research in the study. The fine three-dimensional flowfield and the unsteady characteristic of the large-scale separation will be achieved by experiments and the flow model of the time-averaged flowfield of the large-scale separation will be established. The mechanisms of the formation and vanish of the large-scale separation under the three conditions, which are Mach number change, contraction ratio change and high backpressure, will be experimentally investigated by Mach number changeable wind tunnel. With these studies, the knowledge of the large-scale separation in the unstarted inlet will be improved and the mechanism of the inlet start/unstart will be revealed, which will promote the design and research of the hypersonic inlet.

英文关键词： hypersonic;inlet;unstart;large-scale;separation