为了研究乘波体和进气道的一体化技术，提出了一种新型曲外锥乘波体和进气道的一体化设计方法，在Ma5.5条件下，设计了一体化乘波前体进气道的理论构型。在设计状态，对一体化前体进气道进行了无粘数值仿真，将获得的流场结构及流动参数同理论设计结果进行了对比分析，验证了设计方法的正确性。在马赫数4，5.5和6，攻角-2°～6°内，对一体化构型的基本性能进行了无粘数值仿真，获得的结果表明，该一体化构型具有良好的气动压缩特性。给出了乘波体/进气道一体化设计的新途径，实现了乘波体和进气道符合气动规律的一体化匹配。

For studying the integration issues of waverider and inlet， a novel forebody inlet integration design methodology called Curved Cone Waverider Inlet(CCWI) is put forward. The prototype integrated waverider inlet is designed at free stream Mach number 5.5.The inviscid performances of the designed prototype waverider inlet are simulated by numerical simulation software. The flow field structures and flow parameters are compared with the design results. The validity of present design method is confirmed by the identical simulation and design results. The inviscid performances and flow field structures of the prototype waverider inlet are simulated at Mach number 4， 5.5 and 6， angle of attack from -2° to 6°. Results show that the novel integration configuration has high flow capture ability with good compression performance. The novel waverider inlet integration design method has been put forward in this paper and the waverider/inlet can be integrated according to aerodynamic principles.

国家自然科学基金(51376192)。