吸气式飞行器连续变马赫数风洞试验技术  

Wind tunnel test technique of continuous varying Mach number for air-breathing vehicle

作　　者：周健[1] 张江[1] 陈强[1] 魏巍[1] 刘磊[1] 钱丹丹[1] ZHOU Jian;ZHANG Jiang;CHEN Qiang;WEI Wei;LIU Lei;QIAN Dandan(China Academy of Aerospace Aerodynamics,Beijing 100074,China)

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《实验流体力学》2023年第6期76-85,共10页Journal of Experiments in Fluid Mechanics

摘　　要：为研究吸气式飞行器加/减速引起的进气道起动/再起动现象,以及该过程导致的飞行器整体气动性能突变问题,基于二维楔面激波机理,在1.2 m量级风洞中开展了超声速连续变马赫数试验技术研究,通过研制激波发生与控制系统,实现了一次风洞试验过程中马赫数连续可调。该技术方案具有马赫数调节简单、响应快,马赫数控制可靠、精度高等特点。流场校测表明,瞬时变马赫数区域流场品质满足国军标要求,可开展基于马赫数连续变化的测力测压等风洞试验。在进气道动态特性验证试验中,成功捕获了连续减速状态下进气道由起动到不起动的动态过程,临界状态特性与仿真结果一致性较高。To study the start/unstart phenomenon of the air-breathing vehicle inlet caused by acceleration or deceleration,which also bring the problem of aerodynamic mutation on vehicle,the test technique of continuous varying Mach number was performed in the 1.2 m supersonic wind tunnel based on the flow mechanism of the 2D wedge shock wave.By developing the shock wave generator system,continuous varying Mach number was realized successfully in one wind tunnel test process.And it has also been confirmed that the technical method can make Mach number vary simply and quickly with high quality and precision.Through the flow-field calibration,the quality of the instantaneous flow-field in variable Mach number region meets the standards of GJB eligibly,and thus the field can be used for force and pressure test compliantly.In addition,the test of inlet starting characteristics was carried out and the dynamic process and critical state from start to unstart were captured,which indicates that the test results agree with the numerical simulation accurately.

关 键 词：连续变马赫数 楔面激波 风洞试验 流场校测 吸气式飞行器 进气道 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]