大偏转角时超声速五孔探针激波图谱数值研究  

Numerical Study on Shock Spectrum of Supersonic Five-Hole Probe with a Large Deflection Angle

作　　者：王磊 黄刚锋 阚晓旭 钟兢军 WANG Lei;HUANG Gang-feng;KAN Xiao-xu;ZHONG Jing-jun(Merchant Marine College,Shanghai Maritime University,Shanghai 201306,China)

机构地区：[1]上海海事大学商船学院,上海201306

出　　处：《推进技术》2023年第4期91-100,共10页Journal of Propulsion Technology

基　　金：国家自然科学基金重点项目(52236005);航空发动机及燃气轮机基础科学中心项目(P2022-B-II-007-001)。

摘　　要：激波是超声速流动的关键性问题,而超声速来流条件下气动探针的激波图谱的研究有待进一步丰富。本文以适用于超声速来流条件下的五孔气动探针为研究对象,提出一种复合型五孔压力-温度探针的结构设计方法,并采用经过实验校核的数值方法分析跨、超声速来流绕流探针而形成的激波图谱的变化规律,其中着重关注在正对来流和相对于来流存在较大偏转角度时探针头部及杆体的激波结构。研究结果表明:跨声速来流条件下,探针头部前端会形成一道强度较大的正激波结构;超声速来流条件下,探针与来流存在较大偏转角度时,探针背风面杆体后端会形成“λ”型激波,随着来流马赫数增大最终变为正激波,且激波与附面层相互作用导致探针表面的附面层发生分离,产生了低能流体团。本文的研究成果实现探针头部和杆体激波图谱的再现,充实了超声速探针的基础数据库。Shock wave is the key problem of supersonic flow,and the research on shock wave spectrum of pneumatic probe in supersonic flow condition needs to be further enriched.The five-hole pneumatic probes applicable to supersonic incoming flow conditions was considered as the research object.The structural design method for a composite five-hole pressure-temperature probe was proposed.Numerical methods verified by experiments were used to analyze the variation law of shock wave patterns formed by the probes for transonic and supersonic incoming flow disturbances,with emphasis on the shock wave structure of the probe head and the rod when it was facing the incoming flow and at a large deflection angle with respect to the incoming flow.The results demonstrate that:in the condition of transonic incoming flow,the front of the probe head will form anormal shock wave with stronger intensity.In the condition of supersonic incoming flow,when the probe and the incoming flow have a large deflection angle,a“λ”type shock wave will be formed at the rear end of the rod on the leeward side of the probe.With the increase of the Mach number of the incoming flow,the shock finally becomes a normal shock wave,and the interaction between the shock and the boundary layer leads to the separation of the boundary layer on the probe surface,resulting in a low-energy fluid clusters.The research results of this paper realize the reproduction of the shock wave spectrum of the probe head and rod,and enrich the basic database of supersonic pneumatic probes.

关 键 词：多孔气动探针 五孔探针 跨、超声速来流 结构设计 激波结构 数值模拟 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]