-1- Experimental Investigation on Shock Wave and Turbulent Boundary Layer Interactions in a Square Duct at Mach 2 and 4 Hiromu SUGIYAMA 1 , Koichi FUKUDA 2 , Kazuhide MIZOBATA 3 , Liqun SUN 2 and Ryojiro MINATO 3 1 Department of Mechanical Systems Engineering Muroran Institute of Technology 27-1 Mizumoto, Muroran, Hokkaido 050-8585, JAPAN Phone: +81-143-46-5364, Fax: +81-143-46-5371, E-mail: sugiyama@mmm.muroran-it.ac.jp 2 Graduate School Muroran Institute of Technology 3 Muroran Institute of Technology IGTC2003Tokyo TS-023 ABSTRACT In order to investigate the supersonic internal flows with shock waves, a new supersonic wind tunnel (pressure-vacuum type, Mach 2.0 and 4.0) was designed and constructed in Muroran Institute of Technology. This paper describes firstly outlines of the new Mach 4 supersonic wind tunnel, and describes secondly the location, structure and characteristics of the Mach 2 and 4 pseudo-shock waves in a square duct. The structure and characteristics of the pseudo-shock waves were clarified by color schlieren photographs and duct wall pressure measurements. INTRODUCTION When a supersonic or hypersonic flow in ducts which could be a flow plug, nozzle or combustion heat release interact with downstream blockage devices, “pseudo-shock wave” or “shock-train” are produced as the result of shock wave and wall turbulent boundary layer interactions. The study of pseudo-shock waves has important implications for the design and operation of new air breathing engines for space planes, that is, inlet-combustor isolators for ramjet/scramjet engines, ejector and wind tunnel supersonic diffusers, supersonic centrifugal compressor, and so on. So far, the macroscopic structures and characteristics of pseudo-shock waves in rectangular ducts at the low Mach number (below about Mach number 2) have been studied by many researchers (Ikui et al. (1974), Sugiyama et al. (1987, 1988, 1991, 1995), and Carroll Dutton (1990, 1992)) and the macroscopic structures and characteristics of the pseudo-shock waves were clarified. However, the locations, structures and characteristics of pseudo-shock waves in large size rectangular ducts at the high Mach number (above Mach number 3) have not been fully clarified (Sugiyama et al. (2002)). This paper describes firstly outlines of the new Mach Table 1 Location of the first shock wave and flow confinement Case A Case B Case C X f /D 2.6 7.9 13.6 M =2 /h 0.15 0.25 0.35 X f /D 8.8 13.8 M =4 /h 0.28 0.39 0.47 Copyright © 2003 by GTSJ Manuscript Received on April 9, 2003 1 3 3 4 5 Flow direction 2.Test section 5.Schlieren system 1.Laval nozzle 4.Shock generator 3.Observation window 6.Pressure Measurement system 2 6 Fig.2 Test section for internal flow and measuring system Fig.1 Pressure-vacuum type Mach 4 supersonic wind tunnel Proceedings of the International Gas Turbine Congress 2003 Tokyo November 2-7, 2003