高超声速逆向喷流数值模拟和风洞试验  

Numerical and experimental study on opposing jet in hypersonic flow

作　　者：董昊[1,2] 张旭东 刘是成[1,2] 程克明 赵炜 DONG Hao;ZHANG Xudong;LIU Shicheng;CHENG Keming;ZHAO Wei(College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;Key Laboratory of Unsteady Aerodynamics and Flow Control,Ministry of Industry and Information Technology,Nanjing 210016,China;Computational Aerodynamics Institute of China Aerodynamics Research and Development Center,Mianyang 621000,China)

机构地区：[1]南京航空航天大学航空学院,南京210016 [2]非定常空气动力学与流动控制工业和信息化部重点实验室,南京210016 [3]中国空气动力研究与发展中心计算空气动力研究所,绵阳621000

出　　处：《空气动力学学报》2022年第4期101-109,共9页Acta Aerodynamica Sinica

基　　金：国家数值风洞工程(2020-DY01-001,2018-ZT3B08,2019ZT7-B30);国家自然科学基金(11872208)。

摘　　要：作为一种主动流动控制技术,逆向喷流因其在降低气动热方面的广阔前景而成为研究热点。为探索逆向喷流流动控制技术对高超声速飞行器降热的影响规律及相关机理,对半球体钝体模型进行了不同来流和喷流条件下的数值模拟和风洞试验研究,得到了模型表面的流场和斯坦顿数分布,并对数值模拟和风洞试验结果进行了相互校验。结果表明:逆向喷流产生的降热效果是喷流气体回流和喷流推离头部脱体激波共同作用的结果;在相同来流马赫数下,逆向喷流降热效果随喷流压比的增大而更加显著;在相近喷流压比条件下,来流马赫数越大,逆向喷流降热效果越好。As an active flow control technology,the opposing jet has become a research hotspot due to its broad prospect in reducing aerodynamic heat.In order to explore the heat flux reduction law and related mechanism of opposing jet flow control for hypersonic vehicles,a hemispherical bluff body model was studied by numerical simulations and wind tunnel experiments under different freestream and opposing jet conditions.The flow field and Stanton number distribution on the model surface were obtained,and both numerical and experimental data were verified against each other.The results suggest that,the heat flux reduction effect of the opposing jet is the consequence of a combined action of the jet backflow and the jet pushing away the front shockwave from the head.At a fixed Mach number,the heat flux reduction effect of opposing jet becomes more obvious with the increase of the jet pressure ratio;while under the condition of a similar jet pressure ratio,better heat flux reduction effect by the opposing jet can be achieved at higher Mach numbers.

关 键 词：高超声速 逆向喷流 流动控制 数值模拟 风洞试验 气动热 喷流压比 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程] V211.7