宽速域高超声速气动热风洞理论与技术挑战  

Theroretical and Technical Challenges of Wide Speed Range Hypersonic Aerothermal Wind Tunnel

作　　者：高亮杰 钱战森 王璐 辛亚楠 Gao Liangjie;Qian Zhansen;Wang Lu;Xin Yanan(Aeronautical Science and Technology Key Lab for High Speed and High Reynolds Number Aerodynamic Force Research,AVIC Aerodynamics Research Institute,Shenyang 110034,China)

机构地区：[1]航空工业空气动力研究院高速高雷诺数气动力航空科技重点实验室,辽宁沈阳110034

出　　处：《航空科学技术》2020年第11期66-73,2,共9页Aeronautical Science & Technology

摘　　要：随着可重复使用高超声速巡航飞行器需求的增加,对气动热载荷的评估提出了更为苛刻的要求,需要宽速域高超声速气动热风洞同时具备低扰动、宽马赫数运行、复现总温、气体无污染以及长的有效运行时间等模拟能力。概述了宽速域脉冲型风洞发展现状,对比分析了以Ludwieg管风洞原理运行的优势及所面临的挑战,并针对“可实现性”“可用性”及“好用性”问题,提出了相应的解决措施。With the increasing demand of reusable hypersonic cruise vehicle,the accuracy assessment of aerothermal load is more strict.It required that the wide speed range hypersonic aerothermal wind tunnel has the simulation ability of low disturbance,wide Mach number operation,total temperature recurrence,gas pollution-free and long effective operation time.This paper summarizes the development status of the wide speed range pulse wind tunnel,compares and analyzes the advantages and challenges of the operation based on the principle of Ludwieg tube,and puts forward corresponding solutions to the problems.

关 键 词：宽速域气动热风洞 管风洞 叠加驱动 层流双喷管 

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]