The shock wave/boundary-layer interaction is a common phenomenon, and it occurs in the
internal and external flow fields of the hypersonic vehicle. Then, the separation, the …

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

The research on shock wave/turbulent boundary-layer interactions is mainly limited to
calorically perfect gases; little has been reported on the thermochemical non-equilibrium …

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 …

Global surface pressure measurements have been carried out on a 7° half-angle circular
cone/flare model at nominally zero angle of attack using pressure-sensitive paint (PSP) …

The effect of thermal nonequilibrium on shock interactions of carbon dioxide (CO 2)
hypersonic flows is investigated. Given the relatively low characteristic vibrational …

View Video Presentation: https://doi. org/10.2514/6.2021-0245. vid The Boeing/AFOSR
Mach 6 Quiet Tunnel (BAM6QT) at Purdue University was used to test a sharp cone-cylinder …

Three-dimensional shock wave–boundary-layer interaction arising due to the deflection of a
control surface on a slender cone has been studied at Mach 5 and Mach 8. The control …

This research focuses on measurements of a convective shear-layer instability seen
naturally in quiet hypersonic flow. Experiments were carried out in the Boeing/AFOSR Mach …

A direct numerical simulation of hypersonic Shock wave and Turbulent Boundary Layer
Interaction (STBLI) at Mach 6.0 on a sharp 7° half-angle circular cone/flare configuration at …