激波风洞是空气动力学研究中重要的地面试验设备，其中采用爆轰驱动技术的激波风洞以其较强的驱动能力在高超声速流动试验研究中越来越受到关注。激波风洞的基本配置是激波管，它可以将试验气体迅速升温、增压和加速，能够产生所需要的地球大气环境下的试验气流。随着人类对太空探索需求的不断增长，火星探测已经成为深空探测的热点，然而目前大多数爆轰驱动激波风洞都是以空气为试验气体设计和运行，而不是火星大气的主要成分二氧化碳，需要研究其在进入火星大气环境下的运行特性，另外，对大尺度激波风洞的研究多停留在实验方面，数值模拟其运行状态的关注较少。本文主要利用理论分析和高温热化学反应流动数值模拟技术相结合的研究方法，以JF-12爆轰驱动激波风洞的爆轰驱动段和激波管段为研究对象，对JF-12激波风洞运行的激波动力学过程及缝合运行状态的关键条件参数选取进行了研究，包括波系产生及传播过程、反射激波与接触面的相互作用机制等；并数值研究了JF-12激波风洞在进入火星大气环境下（试验气体更换成二氧化碳）的运行特性；最后进行了其管内激波衰减的粘性耗散机制和模化方法的研究，并完成了粘性计算的风洞运行状态及驻室参数和JF-12风洞实验结果的对比。主要研究工作如下：

1）理论分析上，利用基于理想激波管理论下的等截面及变截面的界面匹配条件计算公式，计算等截面及“小”驱“大”变截面两种结构下以空气或二氧化碳为试验气体时驱动气体声速和缝合激波马赫数之间的关系。计算结果发现，在相同的驱动气体声速条件下，二氧化碳试验气体的缝合激波马赫数要明显高于空气；采用“小”驱“大”的运行方式可以减小缝合激波马赫数。

2）数值研究JF-12激波风洞运行的激波动力学过程及其在进入火星大气环境下驱动二氧化碳的运行特性。利用高温热化学反应流动数值计算技术，对JF-12激波风洞以空气或二氧化碳为试验气体时的运行特性进行了计算模拟，通过改变激波管中驱动和被驱动气体的初始参数及激波管高/低压段的截面积比，来模拟其中的波系产生、传播过程及运行状态，从声阻抗的角度分析了JF-12实验中驱动二氧化碳处于亚缝合运行状态的原因，并定性给出了JF-12激波风洞以二氧化碳为试验气体时实现中低焓值下缝合运行状态关键参数的确定方法。

3）利用准一维计算给出了JF-12风洞激波管内强激波衰减的模化方法，通过在控制方程中添加粘性耗散源项并利用JF-12实验数据对其修正，给出了适用于JF-12激波管段的粘性方程。研究发现，激波管内的粘性耗散具有减小缝合激波马赫数的作用，能够促使激波风洞在较低入射激波强度时保持缝合运行状态，并可以削弱二次激波对风洞驻室气流参数的影响。另外，对粘性方程进行修正之后，现在可以通过准一维粘性计算来模拟并预测JF-12激波风洞运行中入射激波的衰减过程、风洞驻室总压以及有效试验时间。

    Shock tunnels are important ground-based test facilities in aerodynamics research, in which the detonation-driven shock tunnels have attracted more and more attention in the research of hypersonic flows due to their strong driving abilities. Shock tube is the basic configuration of the shock tunnel, which can heat up, pressurize and accelerate the test gas rapidly to produce the required test airflows in the atmosphere of earth. The exploration of Mars is one of the hotspots of the current international deep space exploration which stimulates increasing demand for hypersonic test facilities. However, most of the hypersonic facilities such as the detonation-driven shock tunnels are designed initially for flow tests of air, instead of the carbon dioxide in the Martian atmosphere. Therefore, it’s necessary to investigate their operating characteristics for Mars entry tests. In addition, the research on large-scale shock tunnels mostly concerned in the experimental technology, and less attention are paid to numerical simulation of their operating status. In this work, we mainly used the research method of the combination of theoretical analysis and the numerical calculation technology of high temperature thermochemical reacting flow, to study the shock wave dynamics process and the selection of key parameters for tailored interface condition of JF-12 shock tunnel. The main concerned shock dynamic issues include the wave system generation and propagation process, and the interaction mode between reflected shock waves and contact surfaces can be trimmed for the tailored interface condition. In addition, the operating characteristics of JF-12 shock tunnel for Mars entry aerodynamic tests has been simulated. Finally, the viscous dissipation mechanism and modeling method of shock attenuation in the shock tube are studied, the operating state and chamber parameters of the viscous calculation are compared with JF-12 shock tunnel experimental results. The main research points are listed as follows:

1) In theoretical analysis, based on the ideal shock tube theory, we used the interface matching conditions of constant or variable cross section, to calculate the relationship between the sound speed of driver gas and the tailored shock Mach number for flow tests of air or carbon dioxide, under the two structures of constant cross section and “small” driving “large” variable cross section. It’s found that under the same driving conditions, the tailored shock Mach number of the driving carbon dioxide is significantly larger than that of the driving air. And the operation mode of “small” driving “large” can reduce the tailored shock Mach number.

2) Numerical investigation on the shock wave dynamics and the operating characteristics of driving carbon dioxide in Mars entry tests of JF-12 shock tunnel. We used the numerical calculation technology of high temperature thermochemical reacting flow, to simulate the operating characteristics of JF-12 shock tunnel with air or carbon dioxide as the test gas, by adjusting the driver/driven gas parameters and the cross section area of the driven section, the interaction mode between reflected shock waves and contact surfaces can be trimmed in the simulations. And from the perspective of acoustic impedance, we analyzed the reasons that JF-12 shock tunnel in under-tailored interface condition when driving carbon dioxide, an method to determine the key parameters of tailored interface condition at medium or low enthalpy is given qualitatively when driving carbon dioxide of JF-12 shock tunnel.

3) Through the quasi-one-dimensional calculation, the modeling method of strong shock attenuation in JF-12 shock tunnel is given, the viscous dissipation source term is added into the governing equation and modified by using the experimental data of JF-12, the viscous equation suitable for JF-12 shock tube section is obtained. It’s found that the viscous dissipation in the shock tube can reduce the tailored shock Mach number, which can promote the shock tunnel to maintain tailored interface condition at low incident shock wave intensity, and can eliminate the influence of secondary shock wave on the airflow parameters in the reservoir. In addition, after the revision of the viscous equation, the quasi-one-dimensional viscosity calculation can be used to simulate and predict the shock attenuation process, the total pressure in the reservoir and the effective test time of JF-12 shock tunnel.