Analysis of the Interaction of a Weak Normal Shock Wave with a Turbulent Boundary Layer

Abstract

The method of matched asymptotic expansions is used to analyze the interaction of a normal shock wave with an unseparated turbulent boundary layer on a flat surface at transonic speeds. The theory leads to a three-layer description of the interaction in the double limit of Reynolds number approaching infinity and Mach number approaching unity. The interaction involves an outer, inviscid rotational layer, a constant shear-stress wall layer, and a blending region between them.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1974
Accession Number
ADA012354

Entities

People

  • B. Grossman
  • R. E. Melnik

Organizations

  • Grumman

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Space

DTIC Thesaurus Topics

  • Asymptotic Series
  • Boundary Layer
  • Boundary Value Problems
  • Computational Fluid Dynamics
  • Computational Science
  • Differential Equations
  • Equations
  • Flow Fields
  • Fluid Dynamics
  • Incompressible Flow
  • Mach Number
  • Numerical Analysis
  • Pressure Distribution
  • Pressure Gradients
  • Shear Stresses
  • Skin Friction
  • Turbulent Boundary Layer

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Fluid Mechanics and Fluid Dynamics.