Study on Shock Wave and Turbulent Boundary Layer Interactions in a Square Duct at Mach 2 and 4

作     者：Hiromu SUGIYAMA Ryojiro MINATO Kazuhide MIZOBATA Akira TOJO Yohei MUTO 

作者机构：Department of Mechanical Systems Engineering Muroran Institute of Technology 27-1 Mizumoto Muroran Hokkaido 050-8585 Japan Graduate School Muroran Institute of Technology 

出 版 物：《Journal of Thermal Science》 (热科学学报（英文版）)

年 卷 期：2006年第15卷第1期

页      面：37-42页

核心收录：

学科分类：080704[工学-流体机械及工程] 080103[工学-流体力学] 08[工学] 0807[工学-动力工程及工程热物理] 0805[工学-材料科学与工程（可授工学、理学学位）] 0702[理学-物理学] 0801[工学-力学（可授工学、理学学位）] 

主　　题：supersonic internal flow pseudo-shock wave flow visualization shear stress-sensitive liquid crystal. 

摘      要：In this paper, the outline of the Mach 4 supersonic wind tunnel for the investigation of the supersonic internal flows in ducts was firstly described. Secondly, the location, structure and characteristics of the Mach 2 and Mach 4 pseudo-shock waves in a square duct were investigated by color schlieren photographs and duct wall pressure fluctuation measurements. Finally, the wall shear stress distributions on the side, top and bottom walls of the square duct with the Mach 4 pseudo-shock wave were investigated qualitatively by the shear stress-sensitive liquid crystal visualization method. The side wall boundary layer separation region under the first shock is narrow near the top wall, while the side wall boundary layer separation region under the first shock is very wide near the bottom wall.