ANALYTICAL INVESTIGATION OF FLOW DURATION IN THE CONVAIR HYPERSONIC SHOCK TUNNEL

Abstract

The analytical procedure used to calculate the steady flow duration in a hypersonic shock tunnel is presented. The results of this procedure applied to the Convair Hypersonic Shock Tunnel are given. It is shown that for very low diaphragm pressure ratios, P4/P1 approx. < P4/P1 approx. < 2000, which includes the tailored interface condition the steady flow duration is quite small. This is a result of pressure attenuation caused by the expansion waves reflected from the end of the driver.

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Document Details

Document Type
Technical Report
Publication Date
Jun 10, 1960
Accession Number
AD0681750

Entities

People

  • C. J. Cohan

Organizations

  • General Dynamics

Tags

Communities of Interest

  • Advanced Electronics
  • Air Platforms

DTIC Thesaurus Topics

  • Acoustic Impedance
  • Dynamics
  • Equations
  • Flow
  • Fluid Dynamics
  • High Pressure
  • High Temperature
  • Mach Number
  • Measurement
  • Nozzles
  • Pressure Distribution
  • Shock Tubes
  • Shock Tunnels
  • Shock Waves
  • Steady Flow
  • Thermodynamic Properties
  • Tubes

Fields of Study

  • Physics

Readers

  • Acoustics.
  • Fluid Mechanics and Fluid Dynamics.
  • Software Engineering

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow