高超声速飞行器前体/进气道一体化气动设计回顾与展望  

Retrospect and prospect on the aerodynamic integration of hypersonic aircraft forebody/inlet

作　　者：许耀宇 黄河峡[1] 谭慧俊[1] 蔡佳[1,2] 刘梦莹 王磊 满延进[4] 李宏东 Xu Yaoyu;Huang Hexia;Tan Huijun;Cai Jia;Liu Mengying;Wang Lei;Man Yanjin;Li Hongdong(Key Laboratory of Inlet and Exhaust system Technology,Ministry of Education,College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;College of Aviation Engineering,Nanjing Vocational University of Industry Technology,Nanjing 210023,China;Beijing Aerospace Technology Institute,Beijing 100074,China;Beijing Power Machinery Institute,Beijing 100074,China)

机构地区：[1]南京航空航天大学能源与动力学院进排气技术教育部重点实验室,南京210016 [2]南京工业职业技术大学航空工程学院,南京210023 [3]北京空天技术研究所,北京100074 [4]北京动力机械研究所,北京100074

出　　处：《空天技术》2024年第2期15-38,共24页Aerospace Technology

基　　金：国家自然科学基金(12272177,12025202,U20A2070);国家重大科技专项(J2019-II-0014-0035);青年托举人才项目(2021-JCJQ-QT-064);先进航空动力创新工作站资助项目(HKCX202-02-005);进排气技术教育部重点实验室基金(CEPE2020012)。

摘　　要：高超声速飞行器具有飞行速度快、突防能力强的优点,现已经成为世界各国军事战略及装备发展博弈的焦点之一,前体/进气道一体化气动设计是提升高超声速飞行器/推进系统性能的一个核心途径。综述了升力体/进气道、乘波前体/进气道以及轴对称前体/进气道这3类典型前体/进气道一体化构型的气动设计方法,总结了前体/进气道波系组织、基准流场、流线追踪以及三维非均匀来流条件下前体/进气道波系设计等方面取得的重要进步,这些进步为高超声速前体/进气道的工程设计奠定了重要的理论和方法基础。最后,针对各类前体/进气道一体化构型指出了当前面临的共性问题以及未来的优化方向。Due to its advantages of fast flight speed and strong penetration ability,hypersonic aircraft has become one of the focuses of military strategy and equipment development among countries around the world.The integrated aerodynamic design of the forebody/inlet is a core issue in improving performance of hypersonic aircraft/propulsion systems.An overview of the aerodynamic design methods for typical integrated configurations of lifting body/inlet,waverider forebody/inlet,and axisymmetric forebody/inlet is provided.The significant progress in these areas,including the organization of the forebody/inlet shock system,basic flow field,streamline tracing,and the design of the forebody/inlet shock system under three-dimensional nonuniform inflow conditions are summarised,which lay an important theoretical and methodological foundation for the engineering design of hypersonic forebody/inlet.Finally,the common problems currently faced and future optimization directions for various configurations are pointed out.

关 键 词：高超声速飞行器 升力体 乘波前体 轴对称前体 进气道 一体化 

分 类 号：V211.48[航空宇航科学与技术—航空宇航推进理论与工程]