Accession Number : ADA191546
Title : Theoretical Investigation of 3-D Shock Wave-Turbulent Boundary Layer Interactions. Part 6.
Descriptive Note : Annual rept. 1 Oct 86-30 Sep 87,
Corporate Author : RUTGERS - THE STATE UNIV NEW BRUNSWICK NJ DEPT OF MECHANICAL AND AEROSPACE E NGINEERING
Personal Author(s) : Knight, Doyle D
PDF Url : ADA191546
Report Date : Jan 1988
Pagination or Media Count : 48
Abstract : The research concerns the understanding of 3-D shock wave-turbulent boundary layer interactions. The research activity has focused on several areas. First, the 3-D swept compression corner has been computed at Mach 3 for a sweep angle of 40 deg and compression angle of 24 deg. The calculated flows are in good agreement with experiment. Second, the flowfield structure of the 3-D swept compression corner is dominated by a large vortical structure. Third, the interaction has been found quantitatively to be dominated by inviscid effects except within a small fraction of the boundary layer. Fourth, the effect of boundary layer bleed has been examined for the 3-D shock wave-turbulent boundary layer interaction generated by a sharp fin. The effects of bleed are principally limited to the near surface region. The overall vortical structure is insensitive to surface bleed. Keywords: High speed flows; Viscous-inviscid interactions; Computational fluid dynamics; Navier-Stokes equations.
Descriptors : *BOUNDARY LAYER, *FLOW, *FLUID DYNAMICS, *INVISCID FLOW, *NAVIER STOKES EQUATIONS, ANGLES, COMPRESSION, COMPUTATIONS, FINS, HIGH VELOCITY, INTERACTIONS, SENSITIVITY, SHARPNESS, SURFACES, THEORY, VISCOUS FLOW, VORTICES
Subject Categories : Fluid Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE