超声速湍流混合层中小激波结构的实验研究  

The Experimental Research of Shocklet in Supersonic Turbulent Mix Layer

作　　者：赵玉新[1] 易仕和[1] 何霖[1] 程忠宇[1] 田立丰[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《国防科技大学学报》2007年第1期12-15,共4页Journal of National University of Defense Technology

基　　金：国家自然科学基金资助项目(10672178)

摘　　要：在对流马赫数为1.24的超声速湍流混合层风洞中,以NPLS实验技术为基础观察到了小激波结构。分析了小激波结构产生时的混合层流场参数,给出了从实验图像中确定对流马赫数的方法,避免了理论分析不必要的假设。探讨了小激波结构产生、发展的一般规律。The shocklet was observed based on NPLS techniques in supersonic turbulent mix layer wind tunnel with convective Mach number 1.24. The flow field parameters of mix layer were analyzed with the appearance of shocklet. The method of calculating convective Mach number from experiment image was presented with the consideration that it can avoid unnecessary hypothesis of theory. Finally, the generation and development of shocklet structure were discussed.

关 键 词：超声速湍流混合层 小激波 对流马赫数 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]