上海航天（中英文）2025，Vol.42Issue(1)：169-179,11.DOI:10.19328/j.cnki.2096-8655.2025.01.018
引射工质对高温高超声速层/湍流边界流动的影响
Effects of Injection Gases on High-temperature Hypersonic Laminar/turbulent Boundary Layer Flow
吴心怡 1张伦 1张雨秋 1江中正 1吴昌聚 1陈伟芳1
作者信息
- 1. 浙江大学 航空航天学院,浙江 杭州 310027
- 折叠
摘要
Abstract
The thermal protection of hypersonic aircrafts in flight are under the threat of severe aerodynamic thermal problems.The active thermal protection technology through mass injections can effectively reduce the skin-friction and heat flux on the wall,and thus has become a hot topic in thermal protection research.However,the laws and differences in the effects of injection gases on the high-temperature hypersonic laminar/turbulent boundary layer flow are still unclear,and this is an urgent aerodynamic problem to be solved in active thermal protection design.This paper selects a two-dimensional flat model and adopts the shear stress transport(SST)model to conduct numerical simulation research on the heat flux and skin-friction reduction considering injection gases.The effects of three injection gases,i.e.,water vapor,carbon dioxide,and pyrolysis gas,on the high-temperature hypersonic laminar/turbulent flow are analyzed.The results show that under the pyrolysis gas injection,there are significant differences in the velocity and temperature distributions of the laminar/turbulent shock layer.Compared with no injection,the three gases all effectively reduce the velocity and temperature gradient at the turbulent boundary layer,and then reduce the skin-friction and heat flux on the wall.Compared with the other two gases,the pyrolysis gas has the most significant effects on the skin-friction and heat flux reduction.The research results also indicate that the three gases significantly increase the Reynolds stress and intensify the turbulent fluctuation.关键词
壁面质量引射/剪切应力输运(SST)模型/边界层/降热减阻/化学反应Key words
wall mass injection/shear stress transport(SST)model/boundary layer/heat flux and skin-friction reduction/chemical reaction引用本文复制引用
吴心怡,张伦,张雨秋,江中正,吴昌聚,陈伟芳..引射工质对高温高超声速层/湍流边界流动的影响[J].上海航天（中英文）,2025,42(1):169-179,11.
