Abstract
An experimental study has been conducted to investigate the flow physics along a three-dimensional contour bump in a Mach 1.3 supersonic free-stream. Monochrome Schlieren photography technique was employed for flow diagnostics. Results obtained from the experimental study indicated that the flow pattern appears over the bump upper surface depends on the shock impingement location. It was observed that two lambda shock structures were formed over the bump upper surface in both cases being studied. It was observed that when the normal shock is impinged at the bump crest, the flow downstream of the bump crest remains relatively attached while separated flow appeared downstream of the bump crest for all other normal shock impingement locations.
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 callDisclaimer: 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.
