A Study of Normal Shock-Wave Turbulent Boundary-Layer Interactions at Mach Numbers of 1.3, 1.4 and 1.5.

Abstract

This report presents the results of a study of seven flows involving the interaction between a normal shock wave and a two-dimensional turbulent boundary layer. The measurements were made at free-stream Mach numbers of 1.3, 1.4 and 1.5 and at Reynolds numbers based on an effective streamwise run of 10 to 30-million. The results were obtained from comprehensive traverses with both pilot and static probes. Standard boundary-layer integral parameters based on wall and measured static pressures are presented, together with velocity profiles and the Mach number distribution over the interaction region. An investigation has been made of the 'law of the wall' and the 'law of the wake' under the influence of strong normal pressure gradients.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1982
Accession Number
ADA132033

Entities

People

  • Carol J. Long
  • W. Gregory Sawyer

Organizations

  • Royal Aircraft Establishment

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Space

DTIC Thesaurus Topics

  • Amphibious Military Vehicles
  • Boundary Layer
  • Computational Fluid Dynamics
  • Flow Visualization
  • Fluid Dynamics
  • Fluid Mechanics
  • Intellectual Property
  • Inviscid Flow
  • Measurement
  • Plastic Explosives
  • Pressure Distribution
  • Pressure Gradients
  • Pressure Measurement
  • Supercritical Airfoils
  • Turbulent Mixing
  • Two Dimensional
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Fluid Mechanics and Fluid Dynamics.