Hypersonic laminar flow over a canonical 25°–55° double cone is studied using
computational fluid dynamics and global stability analysis (GSA) with a free-stream Mach …

Hypersonic flow over a two-dimensional compression corner with a Mach number of 7.7 and
unit Reynolds number of 4.2× 106 m− 1 is numerically investigated. Special emphasis is …

Shock-dominated hypersonic laminar flows over a double cone are investigated using time
accurate direct simulation Monte Carlo combined with the residuals algorithm for unit …

The structure of large-scale hypersonic boundary layer separation and reattachment is
studied numerically using a flat plate/compression corner geometry. Apart from verifying the …

A hypersonic shock wave/laminar boundary-layer interaction over a canonical is considered.
Special emphasis is given to the influence of leading-edge bluntness. The results indicate …

This paper describes a numerical investigation on the effects of wall temperature and
leading-edge bluntness on hypersonic laminar separation induced by a finite-span …

The prediction of aero-heating in hypersonic continuum and rarefied gas flows is
challenging work in fluid dynamics. This study introduces Eu-type generalized …

A comprehensive study of the fundamental characteristics of leading-edge separation in
rarefied hypersonic flows is undertaken and its salient features are elucidated. Separation of …

Hypersonic laminar flow separation preceded by a strong expansion can occur in practical
situations such as the base flow of re-entry vehicles and flow over deflected control surfaces …

We investigate the leading-edge separation, also called negligible boundary-layer thickness
separation, induced by an impinging shock on a sharp flat plate. The canonical impinging …