Transition within a Hypervelocity Boundary Layer on a 5-degree Half-Angle Cone in Freestream Air/CO2 Mixtures

Abstract

The most significant instability mechanism which leads to laminar to turbulent transition in hypervelocity flow over cold, slender bodies, characteristic of high enthalpy facilities like the T5 hypervelocity shock tunnel at Caltech, is the so-called second or Mack mode, which depends upon the amplication of acoustic disturbances trapped in the boundary layer, as described by Mack (1984). At high Mach number (>4) and for cold walls, the first (viscous) mode is damped and higher inviscid modes are amplified, so that the second mode would be expected to be the only mechanism of linear instability leading to transition for a slender cone at zero angle of attack.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 2013
Accession Number
ADA587774

Entities

People

  • Graham V. Candler
  • Ivett Leyva
  • Joseph E. Shepherd
  • Joseph S. Jewell
  • Ross M. Wagnild

Organizations

  • Air Force Research Laboratory

Tags

Communities of Interest

  • Energy and Power Technologies
  • Materials and Manufacturing Processes
  • Sensors

DTIC Thesaurus Topics

  • Acoustic Waves
  • Air Force Research Laboratories
  • Boundaries
  • Boundary Layer
  • Boundary Layer Control
  • Computational Fluid Dynamics
  • Computational Science
  • Energy
  • Flow
  • Fluid Dynamics
  • Fluid Mechanics
  • Heat Transfer
  • Layers
  • Mach Number
  • Shock Tubes
  • Shock Tunnels
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers