航空工程进展2024，Vol.15Issue(4)：16-26,11.DOI:10.16615/j.cnki.1674-8190.2024.04.03
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
摘要
Abstract
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 su-personic variable Mach number nozzle is the core component for adjusting Mach number during wind tunnel opera-tion,and its design quality directly determines the flow field quality of the experimental section.The research prog-ress of nozzle design in supersonic variable Mach number wind tunnels both domestically and internationally in re-cent 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 ex-perimental 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 pros-pected.关键词
变马赫数风洞喷管/全柔壁/半柔壁/型面旋转/非对称Key words
variable Mach number wind tunnel nozzle/flexible wall/semi-flexible wall/profile rotation/asymme-tric分类
航空航天引用本文复制引用
王澳,丁浩,田立丰..超声速变马赫数风洞喷管设计研究进展[J].航空工程进展,2024,15(4):16-26,11.基金项目
深圳市科技计划项目资助(ZDSYS20210623091808026) （ZDSYS20210623091808026）
