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

由于高超声速情况下边界层从层流转捩成湍流后, 壁面摩阻和热流出现数倍增长,
控制高超声速边界层使转捩延迟对飞行器减阻降热具有十分重要的意义. 本文首先概述了高 …

Unsteady surface pressure measurements have been carried out on a flat-plate test article in
the Air Force Research Laboratory's Mach-6 Ludwieg Tube at a negative angle of attack …

We investigate by direct numerical simulation the active control of laminar-turbulent
transition in a hypersonic flat-plate boundary layer at a freestream Mach number of 5.86. The …

A novel technique for obtaining quantitative infrared-thermography data on metallic (eg,
aluminum or steel) wind-tunnel models is developed. The methodology incorporates a matte …

Compression corner shock wave/boundary layer interaction (SWBLI) is a typical shock
wave/boundary layer interaction (SWBLI) problem in supersonic/hypersonic flows. In …

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 …

View Video Presentation: https://doi. org/10.2514/6.2023-0096. vid Unsteady surface
pressure measurements have been carried out on a flat-plate test article in the Air Force …

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 …

The nose-tip bluntness effects on the hypersonic crossflow instability were experimentally
investigated over a 7∘ half-angle straight cone at 6∘ angle of attack. The experiments were …