摘要
文章采用热流率测量和纹影拍摄技术,对高超声速层流湍流边界层条件下钝舵干扰流场进行了实验研究.实验在高超声速炮风洞内完成,来流Mach数为6,8.研究结果表明层流与湍流干扰流场之间存在较大差别,层流状态下干扰流场存在分离,平板干扰区内热流率存在负增量,舵面上存在明显的热流率峰值;湍流状态下干扰流场无分离,干扰对平板干扰区内热流率影响较小,舵面上无明显峰值.
An experimental study of interaction flow induced by a swept blunt fin was presented. The tests were carried out in a hypersonic gun tunnel with freestream Mach number of 6 or 8. Schlieren photos and surface heat transfer rate measuring results were obtained. Different features of laminar and turbulent interactive flowfield were presented. For laminar interaction,flow separation can be found,the interference heat transfer rate value ahead of the fin is negative for laminar interaction and an obvious peak value can be found on the fin leading edge. For laminar interaction,attached flow is formed and interference value is small.
出处
《气体物理》
2016年第3期1-5,共5页
Physics of Gases
基金
国家自然科学基金资助(91116009
90816009)
关键词
高超声速流
层流
钝舵
热流率
hypersonic flow
laminar flow
blunt fin
heat transfer rate
