A common denominator between conical-symmetry and conical shock interaction is the
spanwise pressure gradient, which perform more non-uniformity and its interaction flow is …

There are fewer reports on the impinging shock/boundary layer interaction in the high Mach
number and high-temperature flow than that in the supersonic flow. High-temperature flow …

A high-temperature air collisional-radiative model considering both vibrational and
electronic excited states is established to investigate the plasma characteristics along the …

Shock wave/boundary layer interaction (SWBLI) is a common phenomenon occurring in the
supersonic/hypersonic flow fields, and it can constrain the performance of the vehicle. In the …

Magnetohydrodynamic (MHD) heat shield systems have been proven to be highly effective
in hypersonic blunt-nosed bodies. Thus, it is natural to consider the application of MHD to …

To better understand the high temperature non-equilibrium effects of a high Mach number
(above Mach 8) scramjet inlet, the thermal and chemical non-equilibrium flow of Mach 12 …

The high-temperature non-equilibrium effect is a novel and significant issue in the flows over
a high Mach number (above Mach 8) air-breathing vehicle. Thus, this study attempts to …

The high temperature non-equilibrium effects of shock wave interaction and shock
wave/boundary layer interaction are important issues for hypervelocity flows. The models of …

To study the effects of Mach number, Reynolds number and deflection angle on the conical
separation vortex generated by swept shock wave/turbulent boundary layer interaction, the …

THE laminar–turbulence transition is a common phenomenon in a wide range of industrial
systems and is typically accompanied by remarkable growth in the frictional drag and …