摘要
介绍了一种"前缘空腔"高超声速被动流动控制方法并将其应用于轴对称钝锥外形,采用高分辨率的CFD数值模拟方法对不同参数的前缘空腔外形进行了对比研究,阐述了高超声速前缘空腔降低前缘壁面热流的机理,总结了不同空腔参数对空腔外形气动力、热的影响规律。结果表明,合理设计空腔参数可以使空腔外形的前缘壁面热流有较大程度的降低,并且不影响外形的升阻比等气动特性。
Hypersonic flow over the nose of a blunt body with a forward-facing cavity is examined.Comparison analysis is carried out using high resolving CFD numerical simulation method and the mechanism of the cavity heat flux reduction is explained.Operation rules of the different parameters of the cavity are summed up.The results show well designed cavity shape can greatly decrease the leading edge heat flux without affecting the configuration lift-to-drag character.
出处
《空气动力学学报》
EI
CSCD
北大核心
2011年第4期470-475,共6页
Acta Aerodynamica Sinica
基金
国家自然科学基金(90716010)
关键词
高超声速
前缘空腔
数值模拟
气动热
hypersonic
cavity
numerical simulation
aerodynamic heating
