Transonic Shock Interaction with a Tangentially-Injected Turbulent Boundary Layer,

Abstract

A non-asymptotic triple deck theory of transonic shock/turbulent boundary layer interaction is described which takes into account the influence of upstream tangential injection on a curved wall. In addition to Reynolds number and the shock strength, the theory is parameterized by arbitrary values of the incoming boundary layer shape factor, wall jet maximum velocity ratio and the nondimensional height of this ratio; results of a comprehensive parametric study are then presented. It is shown that the wall jet effects significantly reduce both the streamwise scale and displacement thickening of the interaction zone. While increasing the upstream and downstream skin friction levels, these effects also reduce the minimum interactive Cf and thus hasten the onset of incipient separation at the shock foot.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1984
Accession Number
ADA142277

Entities

People

  • A. Deane
  • G. R. Inger

Organizations

  • West Virginia University

Tags

Communities of Interest

  • Air Platforms
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Curvature
  • Displacement
  • Flow Fields
  • Fluid Dynamics
  • Friction
  • Inviscid Flow
  • Mach Number
  • Pressure Distribution
  • Pressure Gradients
  • Reynolds Number
  • Shape
  • Skin Friction
  • Transonic Flow
  • Turbulent Boundary Layer
  • Turbulent Flow
  • West Virginia

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Fluid Mechanics and Fluid Dynamics.