Study of dependence of flow structure in advanced super-surface nozzles from adiabatic indicator

The study of supersonic jets behavior, their structure and properties is one of the most important tasks of gas dynamics. One of the most researched phenomena occurring in many problems of supersonic gas flow is the process of transition from one type of shock wave reflection to another. We obtained the boundaries of the regular and two Mach reflections for the three determining parameters with the help of analytical methods: Mach number, the ratio of specific heats, the ratio of the pressure in the environment to the outlet pressure and the nozzle. The flow of a jet from a supersonic nozzle under various initial conditions and two ratios of specific heats are numerically studied. The influence of these parameters on the flow structure is shown.