A review of fundamental research in combustion stabilization for hypersonic airbreathing
propulsion is presented. Combustion in high-speed airbreathing propulsion systems …

Hypersonic boundary layer transition is a hot yet challenging problem restricting the
development and breakthrough of hypersonic aerodynamics. In recent years, despite great …

Time-resolved surface temperature measurements have been carried out on a 7° half-angle
circular cone/flare model in the Air Force Research Laboratory's Mach-6 Ludwieg Tube …

A sharp, circular 7 half-angle cone was tested in the Boeing/AFOSR Mach-6 Quiet Tunnel at
6 angle of attack, extending several previous experiments on the growth and breakdown of …

The purpose of this research was to design, fabricate, and test a plasma-based active flow-
control system to accelerate and delay crossflow-induced boundary-layer transition on a …

Effective control of hypersonic transition is essential. In order to avoid affecting the structural
profile of the aircraft, as well as reducing power consumption and electromagnetic …

Stationary cross-flow vortex N-factors were calculated over the surface of a yawed circular
cone using computationally predicted and experimentally observed wavenumber …

Cross-flow transition over a delta wing is systematically studied in a Mach 6.5 hypersonic
wind tunnel, employing the Rayleigh scattering flow visualisation, high-speed schlieren and …

View Video Presentation: https://doi. org/10.2514/6.2023-0681. vid The formation and
evolution of a broadband point source disturbance in a Mach 4.82 laminar flow is …

BETWEEN the windward and leeward rays, boundary-layer transition on cones at angle of
attack in hypersonic flow is dominated by the crossflow instability [1, 2], wherein stationary …