Understanding, modeling and control of the high-speed wall-bounded transition and
turbulence not only receive wide academic interests but also are vitally important for high …

The effects of a wavy wall on the stability of a hypersonic boundary layer on a flared cone
are investigated by detailed experimental measurements and direct numerical simulations …

Stability of a supersonic near-wall flow over a shallow grooved plate in the freestream of
Mach 6 is investigated by means of numerical simulations and wind-tunnel experiments …

Hypersonic flow over a two-dimensional compression corner is investigated using
computational fluid dynamics and global resolvent analysis in this study, which is a …

The influence of a wavy wall on the hypersonic boundary layer transition and the related
aerodynamic heating is investigated on a flared cone at a range of unit Reynolds numbers …

THE performance of hypersonic transportation vehicles and reentry vehicles is significantly
affected by the laminarturbulent transition of boundary-layer flows over vehicle surfaces, as …

Direct numerical simulations of a three-dimensional wave packet propagating over a 5.5 deg
compression corner at the freestream Mach number 5.373 are carried out. The Navier …

A method for direct numerical simulation of a laminar–turbulent flow around bodies at
hypersonic flow speeds is proposed. The simulation is performed by solving the full three …

View Video Presentation: https://doi. org/10.2514/6.2022-1578. vid This study explores the
instability waves occuring at Mach 8 on a slender cone with an axial slice that is followed by …

高超声速边界层转捩会使飞行器表面热流和摩阻增加3~ 5 倍, 极大影响高超声速飞行器的性能.
波纹壁作为一种可能的推迟边界层转捩的被动控制方法, 具有较强的工程应用前景 …