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二元高超声速进气道再起动特性研究

Study of Restarting Characteristics of the Two-dimensional Hypersonic Inlet
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摘要 以时均化N-S方程为控制方程,采用变比热容的热完全气体模型和SST湍流模型,对二元混压式高超声速进气道的再起动特性进行了数值仿真。重点分析了来流马赫数、内收缩比、附面层厚度等参数对进气道再起动特性的影响,并详细分析了各因素的作用机制。研究表明,来流马赫数、内收缩比和进入进气道的附面层厚度是决定高超声速进气道再起动特性的关键因素,内收缩比较大、附面层较厚的进气道再起动迟滞回路较宽,再起动马赫数较大;附面层厚度和内收缩比决定了二元高超声速进气道不起动流场的典型特征。 The restarting characteristics of the two-dimensional mixed-compression hypersonic inlet are numerically studied with time-average N-S equations,the thermally perfect gas model,and SST turbulence model. The emphasis is laid on the influence factors such as the Mach number of the incoming gas,the internal contractive ratio of the inlet and the thickness of the boundary layer in the inlet. And the effect mechanism for each factor is analyzed in detail. The results show that the Mach number of the incoming gas,the internal contractive ratio and the thickness of the boundary layer in the inlet are the key influence factors of the restarting characteristics of the hypersonic inlet. The restarting hysteresis loop of the hypersonic inlet with a relatively low internal contractive ratio and thin boundary layer in the inlet is wider,and the corresponding restarting Mach number is higher. The thickness of the boundary layer in the inlet and the inner contractive ratio determine the typical characteristics of the unstart field of the hypersonic inlet.
作者 方传波 张旭荣 余勇 袁天保 蔡辉 Fang Chuanbo, Zhang Xurong, Yu Yong, Yuan Tianbao, Cai Hui (The Equipment Academy of the Rocket Force, Beijing 100091, China)
出处 《战术导弹技术》 北大核心 2017年第5期28-35,共8页 Tactical Missile Technology
关键词 高超声速进气道 再起动特性 来流马赫数 内收缩比 附面层厚度 hypersonic inlet restarting characteristics the Mach number of the incoming gas the internal contractive ratio the thickness of the boundary layer
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