Theoretical Investigation of 3-D Shock Wave-Turbulent Boundary Layer Interactions. Part 6.

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.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1988
Accession Number
ADA191546

Entities

People

  • Doyle D. Knight

Organizations

  • Rutgers University Department of Mechanical and Aerospace Engineering

Tags

Communities of Interest

  • Cyber
  • Energy and Power Technologies
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Computational Fluid Dynamics
  • Flow Fields
  • Flow Visualization
  • Fluid Dynamics
  • Fluid Flow
  • Fluid Mechanics
  • Geometry
  • Mechanical Properties
  • Navier Stokes Equations
  • Shock Waves
  • Three Dimensional
  • Turbulent Boundary Layer
  • Turbulent Flow
  • Turbulent Mixing
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.