【摘要】 高速飞行器在飞行过程中，会出现复杂的激波-激波干扰现象，并导致飞行器壁面区域热流的急剧增大，对飞行器的热防护系统构成了巨大挑战。针对激波-激波干扰带来的极端气动加热问题，将逆向喷流应用于类X-51飞行器进气道唇口，并采用数值模拟方法研究了前体激波干扰下进气道唇口处逆向喷流对流场结构和热流的影响。通过改变来流迎角获得不同迎角下前体激波对唇口激波的干扰类型和对唇口流场与热流分布的影响规律，并进一步研究了不同总压比逆向喷流在Ⅲ、Ⅳ、Ⅴ型激波干扰下的降热特性。结果表明，迎角变化会改变唇口处的激波干扰类型，迎角从3.8°变为4.0°时，干扰类型从Ⅲ变为Ⅳ；逆向喷流可将Ⅲ型激波干扰转换为类Ⅱ型，Ⅳ型激波干扰转换为类Ⅲ型，降低唇口热流；对于Ⅴ型激波干扰，逆向喷流会将其转换为更严重的Ⅳ型干扰，导致壁面热流峰值有所上升。研究获得了不同迎角下类X-51飞行器进气道唇口逆向喷流降热规律，明晰了不同激波干扰类型下逆向喷流的作用机理，可为同类型飞行器热防护设计提供支持。此外，研究结果表明，唇口逆向喷流的引入，会减小进气道总压损失，与无喷相比其总压恢复系数提高49%；同时它还增加了质量流量，有利于提升进气道性能。更多还原

【Abstract】 During the flight of high-speed aircraft, complex shock-shock interference phenomena occur, leading to a sharp increase in the heat flux in the wall area of the aircraft, which poses a huge challenge to the aircraft’s thermal protection system. To address the extreme aerodynamic heating problem caused by shock-shock interference, reverse jet is applied to the inlet lip of an X-51-like aircraft. A numerical simulation method is used to study the influence of the reverse jet at the inlet lip on the flow field structure and heat flux under the interference of the forebody shock. By changing the angle of attack of the incoming flow, the interference types of the forebody shock on the lip shock at different angles of attack and the influence laws on the lip flow field and heat flux distribution are obtained. Furthermore, the heat-reduction characteristics of reverse jets with different total pressure ratios under types Ⅲ, IV, and V shock interferences are investigated.The results show that the change in the angle of attack will change the shock interference type at the lip. When the angle of attack changes from 3.8° to 4.0°, the interference type changes from type Ⅲ to type IV. The reverse jet can convert type Ⅲ shock interference into type-II-like and type IV shock interference into type-IⅢ-like, reducing the lip heat flux. For type V shock interference, the reverse jet will convert it into a more severe type-IV-like, resulting in an increase in the peak wall heat flux. The heat-reduction laws of the reverse jet at the inlet lip of the X-51-like aircraft at different angles of attack are obtained, and the action mechanism of the reverse jet under different shock interference types is clarified, which can provide support for the thermal protection design of the same type of aircraft. In addition, the research results show that the introduction of the reverse jet at the lip will reduce the total pressure loss of the inlet. Compared with the case without jet, the total pressure recovery coefficient is increased by 49%. At the same time, it increases the mass flow rate, which is beneficial to improving the performance of the inlet.更多还原