Shock Wave Penetration and Lateral Pressure Gradient Effects on Transonic Normal Shock-Turbulent Boundary Layer Interactions.

Abstract

The titled affects, which are usually neglected in contemporary theories of viscous-inviscid interaction, are here examined in detail for the unseparated transonic turbulent case. They are found to be significant in many respects. In particular, our results suggest that neglect of shock penetration becomes very inaccurate in the supersonic separated flow regime, leading to substantial underestimates of the local interact strength and its overall streamwise extent. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1976
Accession Number
ADA035573

Entities

People

  • George R. Inger

Organizations

  • Virginia Tech

Tags

Communities of Interest

  • Space

DTIC Thesaurus Topics

  • Boundary Layer
  • Engineering
  • Fluid Dynamics
  • Friction
  • Lepidoptera
  • Mach Number
  • Military Research
  • Pressure Distribution
  • Pressure Gradients
  • Reynolds Number
  • Shock
  • Shock Waves
  • Skin Friction
  • Thickness
  • Turbulent Boundary Layer
  • Turbulent Flow
  • Waves

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Theoretical Analysis.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow