基于型面流场控制的内收缩进气道流场重构与验证

项目名称： 基于型面流场控制的内收缩进气道流场重构与验证

项目编号： No.11502111

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： 王卫星

作者单位： 南京航空航天大学

项目金额： 22万元

中文摘要： 三维内收缩进气道流场参数分布不均，出口流场畸变大，导致进气道性能下降。为进一步提升进气道的性能，本项目拟开展基于型面流场控制的内收缩进气道流场重构研究。初步研究结果显示该设计概念能改善进气道流场结构，提升进气道性能。通过分析三维内收缩进气道流动特征及流动机理，提炼主导该类进气道流动的关键因素； 基于受控型面设计进行流场重构，分析低能流迁移、流向涡产生、发展及传输过程，建立受控型面、波系结构、壁面压力分布、边界层发展与流动特征之间的内在联系，提炼关键型面设计参数，建立流场重构设计准则，揭示基于型面流场控制的流场重构机理；分析流场重构对进气道出口流场、自起动性能及气动性能的影响，发展基于型面流场控制的内收缩进气道流场重构技术并开展风洞试验验证。本项目研究成果将为我国高超声速推进系统相关技术的形成与发展提供理论依据与技术支持。

中文关键词： 内收缩进气道；流场重构；流动机理；型面控制；；气动性能

英文摘要： The uneven distribution of flow parameters and large flow distortion at the exit of inward turning inlet leads to inlet performance degradation. In order to improve the aerodynamic performances of inlet, a study of flow reconstruction based on the shape flow control will to be carried out in this project. The preliminary study shows that the inlet designed with this new concept presents more even flowfield and higher aerodynamic performances. The critical factors that dominate the flow of inward turning inlet will be summarized through analyzing the flow characteristics and flow mechanism. The flow reconstruction is implemented with designing the control-shape, and the migration of boundary layer generation and the development process of streamwise vortex will be analyzed. Base on these, the internal relation among the control-shape, wave structure, wall pressure distribution, boundary layer development and flow characteristics will be established, and the key design parameters of control-shape will be summarized. Further, the design guidelines of flow reconstruction will be set and the mechanism of flow reconstruction based on shape-control will be revealed. Finally, the influence of flow reconstruction on the self-starting capability, aerodynamic performances and flow at exit of inlet will be studied, the technique of flow reconstruction based on shape-control will be developed and verified through wind tunnel test. The achievements of this project will provide design guidelines and technical support for the development of hypersonic propulsion system.

英文关键词： inward turning inlet;flow reconstruction;flow mechanism;shape-control;aerodynamic performance