摘要
研究高超声速层流状态下的钝舵与平板干扰流场特性。通过实验模拟与数值模拟描述了干扰流场的主要特征。模型由平板与钝舵组成,舵后掠角可变。实验在高超声速炮风洞内完成,来流马赫数为7.97,单位雷诺数为5.06~5.89×106(1/m)。通过纹影照像、模型表面压力测量来进行流场结构分析和分布规律研究。数值模拟结果不仅与实验结果进行了比较,还提供了空间流场的细节。研究结果说明了层流状态下干扰流场流动特性及后掠角对流场特性的影响,随着舵前缘后掠角减小,干扰流场尺度、压力峰值载荷增大。
In this paper some features of interactive flow induced by hypersonic laminar flow over blunt fin/flat plate are presented.It is described by experimental and numerical simulation.The experiments were carried out in a hypersonic gun tunnel with freestream Mach number of 7.97 and unit Reynolds number of 5.06～5.89×106m-1.The models consist of a flat plate and fins with different leading edge angle.The schlieren photos and static pressure measured on the model surface were obtained.The results had been compare...
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2007年第6期1472-1477,共6页
Journal of Astronautics
基金
国家自然科学基金项目(10572133)
关键词
钝舵
激波边界层干扰
高超声速流
层流
Blunt fin
Shock wave and boundary layer interaction
Hypersonic flow
Laminar flow
