跨声速叶栅流动中激波与层流边界层干扰的分析与计算  

ANALYSIS AND CALCULATION FOR INTERACTION BETWEEN SHOCK WAVE AND LAMINAR BOUNDARY LAYER

作　　者：方季生 吴文权[2] 

机构地区：[1]美国圣母大学 [2]上海机械学院

出　　处：《工程热物理学报》1990年第2期151-158,共8页Journal of Engineering Thermophysics

基　　金：中国科学院基金

摘　　要：基于实验结果,对流动模型进行了分析。提出了叶栅通道内激波系中“主要分支”的概念。此主要分支位于激波系的前沿。边界层外部流动M数在此发生最剧烈的下降。由于激波系的不稳定,叶栅实验中的非二维性,光学玻璃窗的折射等原因,使纹影照片中激波阴影加宽,而阴影的宽度并不体现激波强度。对包括激波与层流边界层干扰的跨声速边界层的特点进行了讨论,并编制了一个计算程序。用该程序计算了一个典型的超声速入口,M_i=1.34,跨声速叶栅边界层的发展。其结果与实验数据相比,有很好的一致性。进一步证实了所提出的主要分支概念,该计算简便,在UNIVAC-1100机上仅需2—3分钟CPU时间。Based upon the experimental results for transonic flow in cascade, the characteristics of the system of shock waves in the passage of cascade was analyzed and concept of Main Branch of the system was suggested. The named Main Branch is located in the front of the system and where a sharpest decrease of flow mach number occurs. The shade width of the shock wave on the schlieren photograph does not mean the strength of the shock wave, and that is because of the oscillation of the shock wave and the experimental technique problems. The developed method to calculate the interaction between the shock wave and laminar boundary layer was programmed. Numerical test for a typical transonic flow with the interaction between the shock wave and noundary layer was presented, and the agreement with the experimental results is quite good.

关 键 词：叶栅 跨声速 激波 边界层 干扰 

分 类 号：TK263.62[动力工程及工程热物理—动力机械及工程]