高超声速飞行器边界层容易经历层流/湍流转捩, 层流流动和湍流流动在摩擦阻力, 热交换,
噪声和掺混等方面有巨大差别, 转捩问题已成为制约高超声速技术突破的基础科学问题之一 …

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 …

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

Hypersonic boundary-layer instability disturbance and transition experiments were
performed in the Air Force Research Laboratory Mach-6 Ludwieg Tube on a 1-m-long ogive …

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 …

Wind-tunnel experiments were performed to quantify boundary-layer instabilities both on
and off the surface of a 33% scale model of the US Air Force Research Laboratory/US Air …

An experiment investigating the nonlinear breakdown of hypersonic stationary crossflow
waves has been conducted in a Mach 6 quiet tunnel. Secondary instabilities of the stationary …

Boundary-layer stability and laminar-to-turbulent transition are examined on the Boundary
Layer Transition flight-test vehicle using predicted flow conditions at ascent and descent …