EXPERIMENTS ON NON-EQUILIBRIUM SUPERSONIC FLOW SHOCK STAND-OFF DISTANCE OF SPHERES CARRIED OUT IN A NEW TYPE OF INTERMITTENT WIND TUNNEL

Abstract

An experimental investigation of the non-equilibrium behavior of the shock stand-off distance ahead of spheres is described. Wind tunnel experiments using a well understood reacting model gas mixture with a single relaxation process are performed. A marked variation of the dimensionless shock stand-off distance as a function of a non-equilibrium parameter patterned after that proposed by Damkohler is observed. Qualitatively, the results are found to be in agreement with theoretical predictions in the literature. A new application of the Ludwieg tube intermittent supersonic wind tunnel to the study of non- equilibrium flow is presented in the process of this work. The behavior of the intermittent tunnel as a tool is non-equilibrium flow research is calculated in some detail. Experimental results on the facility performance are included for comparison.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1969
Accession Number
AD0687093

Entities

People

  • George Buzyna
  • Peter P. Wegener

Organizations

  • Yale University

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Cameras
  • Diagrams
  • Engineering
  • Equations Of State
  • Flow Fields
  • Fluid Dynamics
  • Free Stream
  • Gas Flow
  • Geometry
  • Hydrodynamics
  • Mach Number
  • Schematic Diagrams
  • Shock Tubes
  • Supersonic Wind Tunnels
  • Test And Evaluation
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Combustion Dynamics and Shock Wave Physics.
  • Combustion science or combustion engineering.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

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