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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。
Taking the time-averaged N-S equation as the governing equation, the thermal-complete gas model with variable specific heat capacity and the SST turbulence model are used to simulate the restart behavior of the BHSH. The effects of Mach Mach number, internal shrinkage ratio and thickness of overburden on the restart characteristics of the inlet were analyzed. The mechanism of each factor was analyzed in detail. The results show that the Mach number, the internal shrinkage ratio and the thickness of the overburden entering the air intake are the key factors that determine the restart characteristics of the high-speed air intake. The larger the internal shrinkage, the thicker the inlet, The starting hysteresis loop is wider and the restarting Mach number is larger. The thickness and internal shrinkage ratio of the overburden determine the typical characteristics of the binary hypersonic inlet non-actuated flow field.