超声速变马赫数风洞喷管设计研究进展  

Research progress in nozzle design for supersonic variable Mach number wind tunnel

作　　者：王澳 丁浩 田立丰 WANG Ao;DING Hao;TIAN Lifeng(School of Aeronautics and Astronautics,Sun Yat-sen University,Shenzhen 518107,China;Shenzhen Key Laboratory of Intelligent Microsatellite Constellation,Sun Yat-sen University,Shenzhen 518107,China)

机构地区：[1]中山大学航空航天学院,深圳518107 [2]中山大学深圳市智能微小卫星星座技术与应用重点实验室,深圳518107

出　　处：《航空工程进展》2024年第4期16-26,共11页Advances in Aeronautical Science and Engineering

基　　金：深圳市科技计划项目资助(ZDSYS20210623091808026)。

摘　　要：超声速变马赫数风洞可在单次运行期间实现马赫数连续调节,对于研究超声速机动过程和超燃冲压发动机起动等问题具有独特的优势。超声速变马赫数喷管是风洞运行期间调节马赫数的核心部件,其设计质量直接决定了实验段的流场品质。本文综述了近些年国内外超声速变马赫数风洞喷管设计的研究进展,介绍了4种典型的变马赫数风洞喷管方案(全柔壁、半柔壁、型面旋转、非对称)的构型设计及其数值模拟和实验标定结果,总结了不同变马赫数风洞喷管方案设计中重点考虑的问题,并对变马赫数风洞喷管在具体实验中的应用进行了展望。The supersonic variable Mach number wind tunnel can operate at multiple Mach numbers during a single operation,which has unique advantages for studying supersonic maneuvering process and scramjet starting.The supersonic variable Mach number nozzle is the core component for adjusting Mach number during wind tunnel operation,and its design quality directly determines the flow field quality of the experimental section.The research progress of nozzle design in supersonic variable Mach number wind tunnels both domestically and internationally in recent years is reviewed in this paper,and four typical variable Mach number wind tunnel nozzle schemes(flexible wall,semi-flexible wall,profile rotation,asymmetric)are introduced,as well as their numerical simulation and experimental calibration results.The key considerations in the design of different variable Mach number nozzle schemes are summarized,and the application ofvariable Mach number wind tunnel nozzle in specific tests is prospected.

关 键 词：变马赫数风洞喷管 全柔壁 半柔壁 型面旋转 非对称 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]