Simulation of Carbon Dioxide Flow Field in Shock Tunnel

Martian spacecraft landing is one of the key technologies of Mars exploration and one of the challenges in the development of Mars lander. The serious challenge is that its aerodynamic environment is far different from the air in Earth's atmosphere. The operation characteristics of the FD-20A shock tunnel under the carbon dioxide flow field are simulated by numerical calculation technology and test measurement. The generation and propagation process of the wave system and the interaction mechanism between the reflected shock wave and the contact surface are simulated by adjusting the initial parameters of the driven and driven gas in the shock tube. The aerodynamic parameters of the driver section and the driven section of the FD-20A shock tunnel are adjusted. By measuring stagnation heat flux at the nozzle exit, combining with theoretical analysis and numerical simulation results of shock tube, nozzle, and test section, the experimental conditions are analyzed with the stagnation parameters of 1140 K and 14.2 Mpa. The test flow fields with Mach numbers of 8.03 at the nozzle exit are obtained.