内转式进气道与飞行器前体的一体化设计综述

飞行器前体/高超声速内转式进气道的一体化设计已经成为吸气式高超声速推进系统研究的一个热点。从气动设计角度分析了高超声速内转式进气道及其与飞行器前体的一体化设计方法。内转式进气道的设计方法主要包括直接流线追踪方法、基于均匀来流的吻切流设计方法和基于前体非均匀来流的内转式进气道设计方法。基于内转式进气道的一体化设计主要包括正对来流的独立进气方式以及利用前体预压缩进气方式两类，结合内转式进气道的设计方法对这两者进行了深入分析。根据分析，基于均匀来流条件的内转式进气道的设计方法得到了深入发展，但还有必要进一步发展非均匀来流条件下的设计方法以提升一体化设计的灵活性；此外，随着内转式进气道设计方法的深入发展，一体化设计也将得到进一步发展。

Overview on integrated design of inward-turning inlet with aircraft forebody

The integrated design of aircraft forebody/hypersonic inward-turning inlet has become a hot spot in the research of airbreathing hypersonic propulsion system. This paper mainly analyzes the design method of hypersonic inward-turning inlet and its integration with aircraft forebody from the perspective of aerodynamic design. For the design method of the inward-turning inlet, it mainly includes direct streamline-tracing method, the osculating method with uniform incoming flow and the inverse design method based on the forebody non-uniform flow-field. The integrated design method based on the inward-turning inlet mainly includes two types:the independent intake mode facing the incoming flow and the pre-compression intake mode with the forebody. Combined with the design method of the inward-turning inlet, the design methods of these two types are analyzed in details. According to the analysis, the design method of the inward-turning inlet based on the uniform forebody flow-field has been further developed, but it is necessary to develop the design method under non-uniform incoming flow to enhance the flexibility of the integrated design. With the in-depth development of the inward-turning inlet design method, the integrated design method is bound to be further developed.