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 …

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

In the design of the hypersonic airliner which can greatly shorten the flight time and conduct
space travel, it is of great significance for a Riemann solver to accurately simulate …

Accurate prediction of boundary layer transition is extremely important for the aerodynamic
and aerothermodynamic design of a hypersonic vehicle. Crossflow instability plays a crucial …

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 …

This work presents a successful implementation of fast-responding pressure-and
temperature-sensitive paints for study of hypersonic shock–body interaction between stage …

A local correlation-based transition model is developed for high-speed transitional flows.
Through an analysis of self-similar solutions for compressible boundary layers, a new …

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 38.1%-scale model of the Hypersonic International Flight Research Experimentation
Program's Flight Five 2: 1 elliptic cone flight vehicle was used to investigate the traveling …