突起物及其干扰区热环境影响范围分析  

Analysis on Thermal Environment of Interaction Region Around Protuberance in High Speed Flows

作　　者：潘宏禄[1] 李俊红[1] 张学军[1] 

机构地区：[1]中国航天空气动力技术研究院,气动热物理研究所,北京100074

出　　处：《计算物理》2013年第6期825-832,共8页Chinese Journal of Computational Physics

摘　　要：针对升力体外形飞行器局部构件干扰流动及热环境影响,采用理论分析、数值模拟、工程半经验模型及实验数据分析相结合,研究高速流动条件下平板表面突起物干扰区气动加热影响.对比分析不同外形特征下突起物对流场结构的影响表明:干扰区热环境分布与流动结构直接相关,压力比拟方法可在局部区域可靠预测热流分布;高台类突起物干扰区范围和热环境敏感依赖于其有效宽度,而低台类突起物干扰区范围和热环境则主要依赖于高度变化;方形头构件与圆形头构件对称面干扰区范围相差1.414倍(湍流/层流均成立);后掠角存在对干扰区范围影响显著,给出后掠角对干扰区的影响关系式.研究结果可方便地用于飞行器热环境预测中,为其提供技术支撑.In hypersonicsupersonic flow conditions, numerical simulations, experience relations and experiment analysis are made to study thermal-environment distribution characteristic around local-parts imposed by protuberance interacting body. Comparing flow characteristic structures in different shape, height, breadth ere, we found that interaction-zone size induced by high protuberance depend sensitively on effective breadth and short protuberance interaction-zone size depend on protuberance height. On the other hand, interaction-zone size is imposed by shade of lead edge, whether laminar or turbulence. Square-lead-surface and arc lead surface separation length ratio is 1. 414. Sweepback affects separation length. A correlative line is built for size of separation imposed by sweepback.

关 键 词：热防护 热环境 局部构件 干扰区 分离流 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]