实验流体力学2026，Vol.40Issue(1)：146-160,15.DOI:10.11729/syltlx20230139
头部温度对圆锥高超声速边界层高频不稳定波影响实验研究
Experimental study of the effect of nose temperature on the disturbance waves in hypersonic boundary layer of blunted cone
摘要
Abstract
The transition of the boundary layer from laminar to turbulent flow significantly impacts the flight stability and safety of aircraft.The aerodynamic heating of the nose of the hypersonic vehicle during flight increases the nose temperature,which affects the stability and transition characteristics of the boundary layer.In this paper,experiments were carried out using a Mach 6,0° angle of attack conical model to explore the influence of the nose temperature and bluntness on the stability of the conical boundary layer.The wall temperature ratio(the ratio of the nose temperature to the total incoming temperature)Tw/T0 varies between 0.6 and 1.3,while the nose bluntness R ranges from 0 to 5 mm.Measurements of boundary layer transition and unstable wave were carried out utilizing infrared thermal imaging and high frequency pulsating pressure sensor(PCB).The experimental results show that changing the nose temperature and bluntness affects boundary layer stability.For a sharp cone(R＜50 μm),the nose heating promotes the development of the second mode wave.However,for R=0.5 mm and 2 mm cones,increasing Tw/T0 from 0.6 to 1.1 inhibits the development of the second mode wave,while a further increase to 1.3 encourages it.For R=5 mm cones,nose heating stabilizes the second mode wave.关键词
高超声速边界层/第二模态/壁温比/红外热成像Key words
hypersonic boundary layer/second mode/wall temperature ratio/infrared thermography分类
数理科学引用本文复制引用
宫铭跃,董昊,刘是成,高思源,焦运..头部温度对圆锥高超声速边界层高频不稳定波影响实验研究[J].实验流体力学,2026,40(1):146-160,15.基金项目
国家数值风洞工程项目(2020-DY01-001,0747-2266SCCMY003) （2020-DY01-001,0747-2266SCCMY003）
