航空学报2026，Vol.47Issue(13)：127-139,13.DOI:10.7527/S1000-6893.2026.33473
基于壁面吹气的高超声速湍流边界层减阻降热
Drag and heat reduction in a hypersonic turbulent boundary layer via wall blowing
陈锦辉 1柳婉婷 1李志远 1蔡淏屹 2吴杰1
作者信息
- 1. 华中科技大学 航空航天学院,武汉 430074
- 2. 湖北航天技术研究院总体设计所,武汉 430048
- 折叠
摘要
Abstract
Hypersonic vehicles are subjected to severe aerodynamic drag and thermal loads during practical flight.To address the issues of high skin-friction drag and intense aerodynamic heating under hypersonic turbulent boundary layer conditions,Large Eddy Simulation(LES)is performed to investigate the drag-and heat-reduction effects of wall micro-blowing through small pores on a Mach number of 6 flat-plate turbulent boundary layer.By comparing smooth-wall and porous-wall configurations,the streamwise distributions of the skin-friction coefficient and wall temperature are analyzed.The results show that wall micro-blowing can simultaneously reduce skin-friction drag and wall thermal load,with the maximum local drag-reduction and heat-reduction rates reaching 17.8%and 7.6%,respectively.Further analysis of the flow-control mechanisms reveals that micro-blowing lifts the mean velocity profile of the turbulent bound-ary layer,redistributes near-wall low-speed fluid toward the outer region,and is accompanied by enhanced stream-wise velocity fluctuations and shear Reynolds stress.Turbulence statistics indicate that micro-blowing intensifies the in-termittency of near-wall turbulence,increases the occurrence probability of ejection events,and strengthens the out-ward transport of low-momentum fluid,which contributes to drag reduction while effectively alleviating wall heat load.These results demonstrate that micro-blowing through small pores has promising potential for simultaneous drag and heat reduction in hypersonic turbulent boundary layers.关键词
高超声速/微吹气/湍流边界层/减阻/降热Key words
hypersonic flow/micro-blowing/turbulent boundary layer/drag reduction/heat reduction分类
航空航天引用本文复制引用
陈锦辉,柳婉婷,李志远,蔡淏屹,吴杰..基于壁面吹气的高超声速湍流边界层减阻降热[J].航空学报,2026,47(13):127-139,13.
