基于前体非均匀来流条件设计的内转式进气道流动机理与控制

For the integrated design of the hypersonic aircraft forebody / inward-turning inlet, the forebody non-uniform flow brings great difficulties to the inlet shock wave configuration and flowfield organization, and seriously damages the performance of the inlet. This research will improve the flowfield structure of the inward-turning inlet to weaken the influence of the forebody non-uniform flow, develop a flowfield structure flexible and controllable inward-turning inlet design method, and carry out the analysis of flow mechanism and exploration of flow control. Firstly, the effects of forebody non-uniform incoming flow on the inward-turning inlet which is designed based on the osculating method are studied, and the main problems and key influence factors of the inlet flow are explored. Secondly, the flowfield structure of the inward-turning inlet is improved, and the inward-turning inlet design and numerical verification are carried out based on the new flowfield structure with forebody non-uniform incoming flow. The flow characteristics of the inward-turning inlet are analyzed based on the new flowfield structure, and the flowfield control method of this inlet is explored. Finally, the wind tunnel test to verify the effectiveness of the project. Through this research, we can deepen the understanding of the inward-turning flow mechanism of non-uniform incoming flow and enhance the ability of the integrated design of the aircraft forebody / inlet.

对于一体化设计的高超声速飞行器前体/内转式进气道，前体非均匀来流给进气道波系配置、流场组织带来较大困难，严重损害进气道的性能。本项目拟改进内转式进气道的流场结构，削弱前体非均匀来流的影响，发展流场结构灵活可控的内转式进气道设计方法，开展流动机理分析与流动控制的探索。首先研究前体非均匀来流对基于吻切流方法设计的内转式进气道流动的影响，探求进气道流动存在的主要问题及关键影响因素；其次对内转式进气道的流场结构进行改进，并在前体非均匀来流条件下基于该新型流场结构进行内转式进气道的设计与数值校验；分析基于新型流场设计的内转式进气道的流动特征，探索流场控制方法；最后开展风洞试验验证本项目的研究效果。通过本项目研究能够加深对非均匀来流条件下内转式进气道流动机理的认识、提升前体/进气道一体化设计的能力。

本项目发展了新型的内转进气道压缩方式解决了飞行器前体与内转进气道一体化设计中前体非均匀流所产生的困难。首先，深入研究了前体非均匀流对传统吻切流方法设计的前体/内转进气道一体化构型的影响，分析应用吻切流方法的改进方向；然后，应用吻切流技术发展了基于前体激波的前体/内转进气道一体化设计方法和基于基本流场非设计特性的前体/内转进气道一体化设计方法；其次，应用课题组发展的CSMP方法开展了“内锥激波+内收缩流场”与“外锥激波+内收缩流场”的前体/内转进气道设计研究，突破了传统内锥激波与低能流相互干扰产生的低能流汇聚问题；最后准备开展风洞试验研究对采用“外锥激波+内收缩流场”的内转进气道设计技术进行验证。通过本项目研究，有效拓展了内转进气道的设计思路，为进气道的压缩方式发展提供参考。