压缩拐角激波边界层干扰热流分布实验研究  

Heat flux distribution in shock wave/boundary layer interactions induced by compression corner:an experimental investigation

作　　者：蔡琛芳 张隽研 沙心国[1] 梁彬[1] 袁湘江[1] CAI Chenfang;ZHANG Junyan;SHA Xinguo;LIANG Bin;YUAN Xiangjiang(China Academy of Aerospace Aerodynamics,Beijing 100074,China)

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《航天器环境工程》2025年第2期167-173,共7页Spacecraft Environment Engineering

基　　金：国家重点研发计划项目(编号:2019YFA0405300)。

摘　　要：激波边界层干扰产生的高热流严重影响飞行器结构安全。为探索激波边界层干扰对高速飞行器热流分布的影响,文章利用红外热图技术,研究了不同后掠角和雷诺数对34°压缩拐角模型激波边界层干扰流场热流分布的影响规律。结果表明:增加后掠角有助于降低流场整体热流峰值,其中中心线热流峰值最大可降低1/3,但小角度后掠模型受后缘弓形激波影响致使局部热流升高,峰值趋近0°后掠模型;雷诺数对激波边界层干扰流场影响显著,表现为雷诺数越高,分离区越小,热流越高。基于上述研究结果,设计时应综合考虑压缩拐角后掠角度以及压缩拐角高度参数,以避开高热流状态,同时加强高热流区域热防护设计。High heat flux generated by shock wave/boundary layer interaction poses a serious threat to the structural safety of aircrafts.To explore the influence of shock wave/boundary layer interaction on the heat flux distributions of hypersonic vehicles,the effects of different sweep angles and Reynolds numbers on a 34°compression corner model were investigated using infrared thermography.The results show that increasing the sweep angle helps to reduce the overall peak heat flux of the flow field,with the peak heat flux on the centerline reduced by up to one third.However,due to the influence of the bow shock wave at the trailing edge,the local heat flux of the models with small sweep angles increases,approaching the peak value of the 0°swept model.Reynolds number has a significant influence on the interference flow field of shock wave/boundary layer interaction,with higher Reynolds numbers leading to smaller separation zones and higher heat fluxes.Based on the results of this paper,the sweep angle and height parameters of the compression corner should be taken into account to avoid high heat flux or strengthen thermal protection design in those regions.

关 键 词：后掠压缩拐角 激波边界层干扰 热流分布 准锥形对称 风洞实验 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]