Non Rankine Hugoniot Shock Zone of Mach Reflection in Hypersonic Rarefied Flows
This study investigates the non Rankine Hugoniot shock zone of Mach reflections in hypersonic flows with different flight altitudes using the direct simulation Monte Carlo method and Navier Stokes approach. In the non Rankine Hugoniot shock zone, the flow viscosity induces the numerical deviation from the inviscid theoretical value with a smooth and continuous variation. It is determined and illuminated by comparing it with shock polars. A suitable and novel definition of the height of the non Rankine Hugoniot shock zone is then derived to facilitate the study of its size. The computations demonstrate that the height of the non Rankine Hugoniot shock zone grows as flight height increases, whereas a reduced Mach stem is observed. The growth of the non Rankine Hugoniot shock zone can be explained by the increase in the curvature of shock waves in the three shock intersection. Computational results show the existence of a strong pressure hot spot and a weak temperature hot spot near the triple point and reve.