This paper deals with the evolution of infrared (IR) thermography into a powerful optical tool
that can be used in complex fluid flows to either evaluate wall convective heat fluxes or …

Laminar–turbulent transition in hypersonic boundary layers has a dramatic effect on heat
transfer, skin friction, and separation. This effect is critical to reentry vehicles and …

LAMINAR-TURBULENT transition in hypersonic boundary layers is important for prediction
and control of heat transfer, skin friction, and other boundary-layer properties. Vehicles that …

In this work, a transition process in a hypersonic flow over a cold-wall compression ramp is
studied using direct numerical simulation (DNS) and global stability analysis (GSA). The free …

Direct numerical simulations (DNS) are performed to investigate a hypersonic flow over a
compression ramp with a free stream Mach number of 7.7 and a free stream Reynolds …

Heat transfer measurements in hypersonic wind tunnels are particularly challenging when
dealing with fully three-dimensional geometries and/or flows with high spatial temperature …

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 …

A sharp leading-edge ramp model with 15°, 20°, and 25° ramp angles is experimentally
investigated at a freestream Mach number 7.7 and a unit Reynolds number 4.2× 10 6 m− 1 …

We investigate the onset of three-dimensionality in a Mach 5 slender-double-wedge flow as
the turn angle at the compression corner increases. Beyond a critical angle, the two …

In this work, the stability of hypersonic flow over a curved compression ramp is studied using
several stability analysis tools and direct numerical simulations (DNS). The free-stream …