Abstract
This paper describes an experimental study on the internal structure of the Mach 4 pseudo-shock wave (PSW) in a straight square duct with cross section of 80×80 mm2, using the new Mach 4 supersonic wind tunnel of Muroran Institute of Technology. The free stream Mach number, unit Reynolds number, and flow-confinement just upstream of the PSW were M∞=3.98, Re=2.6×107 m-1, and δ∞/h=0.39, respectively, where δ∞ is the boundary layer thickness, and h is the half height of duct. The development and characteristics of the turbulent boundary layer on the top and bottom walls of the duct was investigated by LDV measurements. The internal structure of the Mach 4 PSW was clarified by color schlieren photographs and Particle Image Velocimetry (PIV) measurements. It reveals that the turbulent boundary layer on the top or bottom wall of the duct separates in large just after the first oblique shock of the PSW, and the internal flow with the PSW becomes asymmetric flow.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callMore From: TRANSACTIONS OF THE JAPAN SOCIETY OF MECHANICAL ENGINEERS Series B
Disclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
