Accession Number : ADP006051
Title : The Effects of Sweep and Bluntness on a Glancing Shock Wave Turbulent Boundary Layer Interaction,
Corporate Author : COLLEGE OF AERONAUTICS CRANFIELD (UNITED KINGDOM)
Personal Author(s) : Fomison, N. R. ; Stollery, J. L.
Report Date : NOV 1987
Pagination or Media Count : 18
Abstract : An experimental investigation was conducted into the effects of leading edge sweep and bluntness on the flow characteristics of a glancing shock wave turbulent boundary layer interaction generated by a fin-on-plate configuration. A series of sharp swept fins (covering angles of sweep from 0 to 75 deg) and a series of blunt unswept fins (ranging in leading edge diameter from 0 to 25.4 mm) were tested at incidences of up to 30 deg at a Mach number of 2.4 and a freestream Reynolds number of 2.6 million/m. Observations of the mean flow were made using oil flow visualization, static pressure measurements, schlieren photography and vapour screen visualization techniques. In addition, some limited measurements of the unsteady static pressures beneath the interaction were taken. Flow field models are proposed to include the effects of sweep and bluntness and the governing parameters controlling the extent of the distributed flow and the pressure levels beneath the interaction are examined.
Descriptors : *TURBULENT BOUNDARY LAYER, *SWEPTBACK WINGS, INTERACTIONS, BLUNT BODIES, LEADING EDGES, FINS, SHOCK WAVES, FLOW SEPARATION, SCHLIEREN PHOTOGRAPHY.
Subject Categories : Fluid Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE