The basic problems of transition in both incompressible and compressible boundary layers
are reviewed. Flow structures in low-speed transitional and developed turbulent boundary …

高超声速飞行器绕流存在着激波, 边界层, 流动分离, 稀薄气体效应和高温气体效应等多种复杂
流动现象的空气动力学问题, 其中高超声速边界层转捩既是空气动力学的基础问题 …

在过去15 年间, 随着高超声速技术快速发展, 边界层转捩也得到了更加广泛和深入的研究.
人们对流向行波失稳, 横流失稳, Görtler 涡失稳等转捩机理取得了较深刻认识 …

A three-point Focused Laser Differential Interferometer (FLDI) instrument was implemented
to investigate the freestream disturbance environment in a Mach-6 shock tunnel. The FLDI …

The crossflow instability in a hypersonic, laminar boundary layer is investigated using point
measurements inside the boundary layer for the first time. Experiments are performed on a …

The development of disturbances in the boundary-layer transition (BoLT) flight experiment
flowfield is investigated using a recently developed “quiet direct numerical simulation (DNS)” …

The purpose of this paper is to provide secondary instability analysis of stationary crossflow
vortices on a hypersonic yawed straight circular cone with a. At an angle of attack, a three …

Steady laminar flow over a rounded-tip. The flow conditions are selected to match the
planned flight of the Hypersonic Flight Research Experimentation HIFiRE-5 test geometry at …

Direct numerical simulation is performed on a 38.1% scale Hypersonic International Flight
Research Experimentation Program Flight 5 forebody to study stationary crossflow …

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 …