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 …

This paper performs direct numerical simulations of hypersonic boundary layer transition
over a Hypersonic Transition Research Vehicle (HyTRV) model lifting body designed by the …

View Video Presentation: https://doi. org/10.2514/6.2021-0366. vid The transition of a
laminar to turbulent boundary layer plays an important role in the design of hypersonic …

In the present study, we performed direct numerical simulations for a hypersonic turbulent
boundary layer over the windward side of a lifting body, the HyTRV model, at Mach number …

Cross-flow transition over a delta wing is systematically studied in a Mach 6.5 hypersonic
wind tunnel, employing the Rayleigh scattering flow visualisation, high-speed schlieren and …

攻角变化是真实飞行条件下常见的飞行变量之一, 由此引起的流动结构, 热力分布等特征变化
不可忽视. 为研究攻角对于流向涡失稳相关的三维边界层转捩的影响, 选用长短轴比为4: 1 …

The wall heat flux (WHF) in the hypersonic boundary layer over the windward side of a lifting
body, namely, the hypersonic transition research vehicle model, is comprehensively …

High-fidelity computational fluid dynamics of hypersonic flow over a swept wedge model
were performed to investigate the origin mechanisms of heat streaks emanating from the …

View Video Presentation: https://doi. org/10.2514/6.2023-0438. vid This work details
ongoing efforts at the NASA Langley Research Center to develop and validate a general …

横流效应显著影响高超声速飞行器的三维边界层转捩过程, 深化对该流动机制的认识有助于提升
和改善飞行器气动性能及热力学环境. 针对HIFiRE5 椭圆锥绕流问题, 采用大涡模拟方法计算 …