AN EXPERIMENTAL STUDY OF BOUNDARY LAYER PARAMETERS AT THE EXIT OF A HYPERSONIC CONTOURED NOZZLE.

Abstract

The boundary layer thickness and displacement thickness were experimentally evaluated at the exit plane of an arc heated 9.492 inch exit diameter hypervelocity (M> or =8) contoured nozzle for both equilibrium and nonequilibrium flows. It was concluded that the boundary layers were turbulent and the use of a plenum chamber decreases the displacement thickness for identical arc heater stagnation chamber conditions. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1965
Accession Number
AD0621024

Entities

People

  • James Daryl Cox

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Arc Heaters
  • Boundaries
  • Boundary Layer
  • Chambers
  • Diameters
  • Displacement
  • Flow
  • Heaters
  • Layers
  • Nonequilibrium Flow
  • Plenum Chambers
  • Thickness

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Fluid Dynamics.

Technology Areas

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