Experimental Research on Swept Shock Wave/Boundary Layer Interactions

Abstract

An experimental research effort on the subject of swept shock wave interactions with turbulent boundary layers is reported. The research relied largely on non-intrusive, laser-based optical flow diagnostics. Experiments were carried out to define the Mach number influence, flowfield structure, and quantitative skin friction behavior of fin-generated swept interactions over the supersonic range from March 2.5 to 4.0, including weak, moderate, and strong interactions. The results of this research have given new insight into the fin- interaction flowfield structure, which involves a jet-impingement process caused by shockwave bifurcation. High skin friction levels were measured in the vicinity of this jet impingement and were used for the validation of computational predictions carried out by others.

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Document Details

Document Type
Technical Report
Publication Date
Jun 28, 1989
Accession Number
ADA211744

Entities

People

  • Gary S. Settles

Organizations

  • Pennsylvania State University

Tags

Communities of Interest

  • Air Platforms
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Computational Fluid Dynamics
  • Flow Visualization
  • Fluid Dynamics
  • Gas Dynamics
  • Interferometers
  • Lasers
  • Light Sources
  • Mach Number
  • Mechanical Engineering
  • Physics Laboratories
  • Pressure Distribution
  • Pulsed Lasers
  • Test Facilities
  • Turbulent Boundary Layer
  • Turbulent Mixing
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Directed Energy
  • Hypersonics
  • Hypersonics - Hypersonic Flow