实验流体力学2025，Vol.39Issue(5)：88-99,12.DOI:10.11729/syltlx20240013
HyTRV标模迎风面马赫6边界层转捩实验
Mach 6 boundary layer transition experiment on windward side of a HyTRV model
摘要
Abstract
The study of boundary layer transition is extremely important in the design of high-speed vehicles,and it is currently one of the most popular research topics.The experiments for a HyTRV(Hypersonic Transition Research Vehicle)model under Mach 6 are conducted in a wind tunnel.The effect of surface roughness,angle of attack,and unit Reynolds number on the transition of the HyTRV windward is studied using infrared thermography and numerical simulation.The experimental findings of the same model in two wind tunnels are compared.The results reveal that increasing the surface roughness has less effect on the transition position,with roughness states of 1,3 and 6 μm.Increasing the angle of attack(within the tested range of 0-6 degrees)effectively suppresses crossflow transition while promoting centerline streamwise vortex transition.Moreover,increasing the unit Reynolds number promotes both crossflow and centerline vortex transition,leading to higher transition Reynolds numbers.Notably,the transition position of the same model varies considerably in different wind tunnels.For the same unit Reynolds number,the transition Reynolds number of the wind tunnel with a large nozzle-exit scale is higher than that of the wind tunnel with a small nozzle-exit scale.关键词
HyTRV标模/边界层转捩/风洞实验/攻角/单位雷诺数/表面粗糙度Key words
HyTRV standard model/boundary layer transition/wind tunnel experiments/angle of attack/unit Reynolds number/surface roughness引用本文复制引用
涂国华,王傲,刘姝怡,黄刚雷,段茂昌,徐洋,陈坚强..HyTRV标模迎风面马赫6边界层转捩实验[J].实验流体力学,2025,39(5):88-99,12.基金项目
国家自然科学基金项目(920523101) （920523101）
国家自然科学基金青年基金项目(12202477) （12202477）
