Surface Roughness Effects on the Hypersonic Turbulent Boundary Layer.

Abstract

An experimental investigation of the response of a hypersonic turbulent boundary layer to a step change in surface roughness has been performed. The boundary layer on a flat nozzle wall of a Mach 6 wind tunnel was subjected to abrupt changes in surface roughness and its adjustment to the new surface conditions was examined. Both mean and fluctuating flow properties were acquired for smooth-to-rough and rough-to-smooth surface configurations. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1977
Accession Number
ADA042141

Entities

People

  • Dale E. Berg
  • Toshi Kubota

Organizations

  • California Institute of Technology

Tags

Communities of Interest

  • Advanced Electronics
  • Counter IED

DTIC Thesaurus Topics

  • Boundary Layer
  • Boundary Layer Flow
  • Equations
  • Fluid Dynamics
  • Fluid Flow
  • Hypersonic Flow
  • Mach Number
  • Measurement
  • Reynolds Number
  • Skin Friction
  • Surface Properties
  • Surface Roughness
  • Surfaces
  • Turbulent Boundary Layer
  • Walls
  • Wind
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

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