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.

Report Date:

1988-01-01

Pagination or Media Count:

48.0

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