随着临近空间高超声速飞行技术的发展, 预测高超声速边界层转捩位置的需求变得越来越迫切.
由于高超声速实验很难做, 不可能做得很多, 因此像低速飞行器那样的半经验预测方法恐怕很难 …

This article reviews the hypersonic laminar-turbulent boundary layer transition over a blunt
circular cone under support of the National Key Research and Development Program of …

Boundary layer transition over a lifting body of 1.6 m length at. The model geometry is the
same as the Hypersonic Transition Research Vehicle designed by the China Aerodynamics …

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 …

Compared to the streamwise instability, the cross-flow instability in high-enthalpy flows has
received relatively less attention, but the latter is of vital importance in the flow transition for …

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 secondary instabilities of stationary cross-flow vortices in a Mach 6 swept wing flow are
studied using Floquet theory. High-frequency secondary instability modes of 'y'mode on top …

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 …

A new type-II secondary instability mode was recently identified in high-speed cross-flows
using stability analysis, but its role in the transition process is not yet clear. Here, the …

An investigation into the linear instability of streamwise vortices over a yawed blunt cone
with a half-angle of 7 at 6 angle of attack, a free-stream Mach number of 6, and a Reynolds …