This work presents a detailed analysis of the shock wave/boundary layer interaction in
hypersonic flows around a double-cone. Numerical simulations have been carried out by …

Laminar hypersonic flows at Mach 7.10 with unit Reynolds numbers of 5.2× 10 4, 1.04× 10
5⁠, and 4.14× 10 5 m− 1 over a 30/55 double-wedge configuration were studied to …

Boundary layer separation is a common challenge in fluid dynamics, where flow separates
from a surface due to adverse pressure gradients. Transpiration, the injection or suction of …

In this article, the authors present an experimental investigation of the thermochemical
relaxation regions downstream of symmetric Mach reflections generated in Mach 8.5 flows …

The characterization of the shock interaction mechanism originating from the high-Mach
nonequilibrium flow over double-wedge geometries is key to the design of hypersonic …

A high-temperature effect is crucial in cold-to-hot correlation for thrust nozzles to employ
experimental data of cold flow to predict the real flight performance of hot gas. The high …

As a classic aerodynamic phenomenon, shock-shock interferences (SSI)[1-6] widely present
in high-speed vehicles' internal and external flow fields. This phenomenon has received …

In this study, shock stand-off distances for thermally and chemically non-equilibrium flows of
nitrogen over wedges are computationally investigated via a hypersonic computational fluid …

Numerical simulations of inviscid hypersonic flow over a double-wedge geometry are
conducted. High temperature effects are studied using a local thermodynamic equilibrium …

This paper is devoted to the description of computational algorithms for modeling quasi-one-
dimensional non-steady flows of a multicomponent reacting gas. The particularity of the …