摘要
以N-S时均化方程为控制方程,引入变比热容的热完全气体模型,采用k-ωSST湍流模型及自适应网格加密技术,对高超声速进气道再起动过程进行了二维准定常数值仿真研究。结果发现,当内收缩比较大时,分离激波即使打入唇口,大规模流动分离仍存在,须继续增加来流马赫数(M∞),才能使进气道完全起动,即进气道可能存在没有溢流的不起动流场结构,这在已发表文献中还少有提及。深入分析表明,决定高超声速进气道再起动的关键因素是分离区前体形状和分离区后部逆压梯度,前者类似于一个虚拟楔面,楔角及分离激波角大小主要由附面层和来流条件决定,随M∞的增加而减小;后者主要受进气道内型面及内收缩比影响,对分离区大小及溢流量起决定作用。
Using the time-averaged N-S equation as the control equation,and using the thermally perfect gas model,the 2-D flow of hypersonic inlet during the restarting was numerically simulated by means of k-ω SST turbulence model and adaptive mesh technique.The results show that the inlet will not restart immediately even if separation shock has entered the lip,when the internal contraction ratio is large enough,which means that there is a unstart flow with no mass spilling.The deeply research shows that the key influencing factors of inlet restarting process are shape and adverse pressure gradient of separation bubble.The former,which is similar with a virtual wedge,is decided by boundary layer and incoming mach number,and decrease with the increasement of incoming mach number;the latter,which decide the magnitude of separation bubble and spilling,is influenced by inlet inner structure and contraction ratio.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2011年第2期161-166,共6页
Journal of Solid Rocket Technology
关键词
高超声速进气道
再起动特性
分离激波
内收缩比
hypersonic inlet
restart performance
separation shock
internal contraction ratio
