Supersonic Boundary Layer Stability over a Rough Wall.

Abstract

Measurements of the growth or damping of natural disturbances in a laminar boundary layer at Mach 3 have been made. Unit Reynolds number and roughness effects have been documented. A primary mode, three dimensional unstable region was identified which has a minimum critical Reynolds number of 180. Amplification rates within this region agree well with theory except that show higher amplification than expected. A second unstable region was discovered between this region and the transition onset defined by the first departure from laminar similarity. Much higher frequencies and amplification rates are found in this region. Increasing unit Reynolds number decreases overall amplification rates and increases transition distance. Random roughness was found to unsuitable for stability studies. Keywords: Supersonic flow.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1985
Accession Number
ADA179580

Entities

People

  • A. Demetriades

Organizations

  • Montana State University

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Amplitude
  • Boundary Layer
  • Boundary Layer Control
  • Engineering
  • Flow
  • Fluid Dynamics
  • Frequency
  • Geometry
  • Leading Edges
  • Measurement
  • Mechanical Engineering
  • Surface Roughness
  • Three Dimensional
  • Turbulence
  • Turbulent Mixing
  • Two Dimensional
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers