摘要
介绍了中国科学院高温气体动力学实验室JF-16爆轰驱动高焓激波膨胀管的研制进展及其性能测试结果.性能研究主要测量了入射激波速度和压力曲线.根据入射激波速度,应用Mirels的黏性激波管理论计算了超高速试验气流的运动速度,然后应用Gaseq软件计算了试验气流的热力学参数.研究结果表明:在16.35 m长的JF-16激波膨胀管中获得了流速7000 m/s以上的稳定试验气流,试验时间为50～100μs,试验气流总焓30MJ/kg左右.
The performance of the detonation-driven high-enthalpy shock expansion tube （JF-16）, manufrac- tured recently in LHD of Chinese Academy of Sciences, was experimentally investigated to obtain the velocity and the pressure of the incident shock speed. The velocity and other thermodynamic parameters of the hy- pervelocity test flow was predicted with Mirels＇ theory and the Gaseq software, respectively. The experimental results show that the test flow with a velocity of above 7 000 m/s, an effective test duration between 50-100μs and the total enthalpy up to 30 MJ/kg have been achieved with JF-16 shock expansion tube of 16.35 m length.
出处
《力学学报》
EI
CSCD
北大核心
2008年第4期473-478,共6页
Chinese Journal of Theoretical and Applied Mechanics
基金
国家自然科学基金(90205027，10276035)~~
关键词
激波膨胀管
爆轰驱动
超高速流动
入射激波
性能测试
shock expansion tube, detonation-driver, hypervelocity flow, incident shock, performance test
