内凹通道中激波串流场特性的实验研究  

Experimental Study on Shock Train Characteristics in Concave Channels

作　　者：信宣安 王子傲 常军涛[1] 王刚[2] XIN Xuanan;WANG Ziao;CHANG Juntao;WANG Gang(Institute of Advanced Power Technology,Harbin Institute of Technology,Harbin Heilongjiang 150001,China)

机构地区：[1]哈尔滨工业大学先进动力技术研究所,黑龙江哈尔滨150001 [2]中国空气动力研究与发展中心超高速所,四川绵阳621000

出　　处：《海军航空大学学报》2024年第3期350-356,共7页Journal of Naval Aviation University

摘　　要：三维内转式进气道以其高总压恢复系数和高压缩效率等优势,已成为高超声速进气道的发展趋势。然而,内转式进气道流场中更为复杂的激波串结构以及激波串/边界层相互作用成为其性能发挥的关键制约因素。针对内转式进气道中复杂的流动特性,文章开展了高超声速地面风洞实验研究,并对流场进行了可视化测量。首先,搭建了超声速直连式风洞实验台;然后,设计了方转圆段将内转式进气道中独特的内凹通道和矩形喷管平滑连接。结果表明:低来流马赫数下,内凹通道中的激波串前缘激波呈“λ”型,高来流马赫数下则呈“X”型,并且平直壁侧发生流动大分离,流场具有显著非对称性。此外,随着背压的增加,激波串继续向前移动,前缘激波扫掠时的测量点压力发生显著的振荡跳跃。The three-dimensional internal rotating inlet has become the development trend of future hypersonic inlets due to its advantages such as high total pressure recovery coefficient and high compression efficiency.However,the more complex shock train structure and shock train/boundary layer interaction in the flow field of an internal rotating inlet be‐come key constraints on its performance.In response to the complex flow characteristics in an internal rotating inlet,hy‐personic ground wind tunnel experiments are conducted and measurements of the flow field are visualized.Firstly,a su‐personic direct connected wind tunnel experimental platform is built;secondly,a square to circular section is designed to smoothly connect the unique concave channel and rectangular nozzle in the inner rotating inlet.The final results indicate that the shock wave at the leading edge of the shock train in the concave channel is of type“λ”at low Mach numbers and of type“X”at high Mach numbers,and large flow separation occurs on the flat wall side,resulting in significant asymme‐try in the flow field.In addition,as the back pressure increases,the shock wave train continues to move forward,and the pressure at the measurement point where the leading edge shock wave reaches undergoes a significant oscillation jump.

关 键 词：内转式进气道 内凹通道 激波串 前缘激波 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]