JF-22超高速风洞理论基础与关键技术  

Theoretical bases and key technologies of JF-22 hypervelocity wind tunnel

作　　者：姜宗林[1,2] 韩桂来 汪运鹏[1] 刘云峰 苑朝凯 罗长童[1] 王春 胡宗民 刘美宽[1] JIANG Zonglin;HAN Guilai;WANG Yunpeng;LIU Yunfeng;YUAN Chaokai;LUO Changtong;WANG Chun;HU Zongmin;LIU Meikuan(State Key Laboratory of High Temperature Gas Dynamics,Institute of Mechanics,Chinese Academy of Sciences,Beijing 100190,China;School of Engineering Science,University of Chinese Academy of Sciences,Beijing 100049,China)

机构地区：[1]中国科学院力学研究所空天飞行高温气动全国重点实验室,北京100190 [2]中国科学院大学工程科学学院,北京100049

出　　处：《航空学报》2025年第5期136-151,共16页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(11727901,11532014,12072353,12132017)。

摘　　要：国内外高超声速飞行关键技术的验证与考核一直都依赖于飞行试验,费时、昂贵、又具有后验性。几十年来,发展先进的高超声速地面试验装置一直是一个基础性的空气动力学前沿课题。目前世界上能够开展高马赫数飞行条件下的吸气式高超声速发动机试验的风洞试验能力依然不足,国家自然科学基金委员会国家重大科研仪器项目支持的JF-22超高速风洞的研制成功是一个重大突破。首先,综述了高超声速风洞研发的需求背景,介绍了基于工程实际的4项基本需求。并针对热化学反应气体流动,论述了空气动力学试验模拟准则从“流动相似”到“飞行条件复现”变革的必要性。然后,阐述了爆轰驱动超高速激波风洞理论,由此建立的激波风洞关键技术,及其解决的工程问题。最后,总结了在这个理论基础上构建的JF-22超高速风洞技术体系及其达到的主要性能指标和风洞调试结果。这些风洞调试结果既是对爆轰驱动超高速激波风洞理论的验证,也是对JF-22超高速风洞技术体系的综合考核。JF-22超高速风洞的高流速、高总温、高总压特色及其宽速域与宽空域性能,对于开展吸气式高超声速发动机与天地往返可重复使用空天飞行器的研发,推动高温气体动力学科前沿的拓展具有重要意义。The assessment of hypersonic flight technology at home and abroad always relies on flight tests,which are time-consuming and expensive,and have posterior risks.The development of advanced hypersonic ground test facili⁃ties has been a fundamental research topic in aerodynamics frontier for decades;however,the existing test facilities are still inadequate for the required technology development of air-breathing hypersonic engines at high Mach num⁃bers.The successful development of the JF-22 hypervelocity wind tunnel under the National Major Scientific Research Instrument Project supported by the National Natural Science Foundation of China is a major breakthrough in this area.This paper first reviews the research background of the hypersonic wind tunnel and introduces the four basic re⁃quirements of the wind tunnel based on engineering practice.Considering thermo-chemically reacting gas flows,the necessity of revolutionary change of the wind tunnel test simulation criteria of experimental aerodynamics from“flow similarity simulation”to“flight condition reproduction”is discussed.Then,the theories and technologies for detonationdriven hypervelocity shock tunnels are systematically expounded,and the engineering problems solved with the theo⁃ries and technologies are also discussed.Finally,the technology system of the JF-22 hypervelocity wind tunnel,de⁃veloped on the basis of these theories is summarized and evaluated with the JF-22 calibration results.These results not only verify the theories of detonation-driven hypervelocity shock tunnel,but also show a comprehensive assess⁃ment of the JF-22’s technology system.The success of the JF-22 hypervelocity wind tunnel is a new milestone in de⁃veloping advanced hypersonic test facilities.The JF-22 remarkable performances,such as high flow velocity,high to⁃tal temperature and high stagnation pressure,and wide speed range and altitude are of significance for supporting the research on air-breathing hypersonic engines,aerospace aircrafts,and the fron

关 键 词：正向爆轰驱动 化学反应气体流动 超高速激波风洞 激波膨胀加速 吸气式高超声速发动机 空天飞行器 

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] V241