Three-Dimensional Shock Wave-Turbulent Boundary Layer Interactions at Mach 6

Abstract

Experimental results of an investigation of the three-dimensional interaction between a skewed shock wave and a turbulent boundary layer are presented. Surface pressure and heat transfer distributions and oil flow photographs were obtained at a freestream Mach number of 5.85 and two Reynolds numbers of ten and twenty million per foot. The model configuration consisted of a shock generator mounted perpendicularly to a flat plate. The shock generator leading edge was sharp and nonswept and intersected the flat plate surface about 8.5 inches downstream of the flat plate leading edge. The shock generator surface was 7.55 inches long and 3 inches high and its angle to the freestream flow was adjusted from 4 to 20 degrees. The generated shock waves were of sufficient strength to produce turbulent boundary layer separation on the flat plate surface.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1975
Accession Number
ADA014738

Entities

People

  • C. H. Law

Organizations

  • Air Force Research Laboratory

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Aerodynamics
  • Air Force
  • Boundary Layer
  • Calorific Value
  • Coordinate Systems
  • Flow Fields
  • Flow Visualization
  • Fluid Dynamics
  • Heat Transfer
  • Instrumentation
  • Inviscid Flow
  • Mach Number
  • Pressure Distribution
  • Pressure Gradients
  • Three Dimensional
  • Turbulent Boundary Layer
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.