Shock-Boundary Layer Interaction Effects in Transonic Flow Fields.

Abstract

This report summarizes the results of a five-year basic theoretical study of non-separating transonic shock-turbulent boundary layer interactions. Both local and downstream boundary layer distortion effects have been studied including extensive comparisons with available experimental data. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Jan 25, 1980
Accession Number
ADA080889

Entities

People

  • George R. Inger

Organizations

  • Virginia Tech

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Configurations
  • Airfoils
  • Boundary Layer
  • Boundary Layer Flow
  • Computer Programs
  • Equations
  • Flow Fields
  • Hydrodynamics
  • Inviscid Flow
  • Mach Number
  • Pressure Distribution
  • Pressure Gradients
  • Reynolds Number
  • Skin Friction
  • Supercritical Airfoils
  • Turbulent Boundary Layer
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.
  • Technical Research and Report Writing.