Instability measurements of an axisymmetric, laminar separation bubble were made over a
sharp cone-cylinder-flare with a flare angle under hypersonic quiet flow. Two distinct …

Instabilities generated in Mach-6 quiet flow about an axisymmetric cone-cylinder-flare
geometry with a 5∘ half-angle sharp cone were studied in the Boeing/AFOSR Mach-6 Quiet …

Boundary layer transition over a lifting body of 1.6 m length at. The model geometry is the
same as the Hypersonic Transition Research Vehicle designed by the China Aerodynamics …

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 …

The effects of a wavy wall on the stability of a hypersonic boundary layer on a flared cone
are investigated by detailed experimental measurements and direct numerical simulations …

We utilize resolvent and weakly nonlinear analyses in combination with direct numerical
simulations (DNS) to identify mechanisms for oblique transition in a Mach hypersonic flow …

Transitional shockwave/boundary layer interactions (SBLI) are studied experimentally.
Experiments are conducted on a hollow-cylinder flare model in the R2Ch blowdown facility …

Hypersonic flow over a two-dimensional compression corner is investigated using
computational fluid dynamics and global resolvent analysis in this study, which is a …

Experiments are performed in a Mach-6 shock tunnel to examine the laminar-to-turbulent
transition process associated with a sudden increase in surface angle on a slender body. A …

Computations are performed to investigate the convective and global boundary-layer
instabilities over a sharp cone–cylinder–flare model at zero-degree angle of attack. The …