DESIGN FEATURES OF THE GENERAL ELECTRIC RESEARCH LABORATORY HYPERSONIC SHOCK TUNNEL

Abstract

Design features of the General Electric Research Laboratory hypersonic shock tunnel are described. Particular emphasis is placed on many of its unique features. The loading and ignition system for consistent driver combustion without detonation is discussed. The anchoring of the driver and the slip joint clamping section that holds the main scored diaphragm is described in some detail. By boring and honing the stainless steel tubes, the attenuation of the shock wave in the long driven section was minimized. The use of a second diaphragm and a slip joint at the entrance to a conical nozzle is explained. The development of instrumentation necessary for shock tunnel operation is shown to have progressed to a point where the hypersonic shock tunnel is an extremely useful and versatile tool for hypersonic research. It is possible to simulate the Mach numbers and temperatures encountered by ICBM's, satellites, and space vehicles at the high altitude conditions.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1961
Accession Number
AD0600345

Entities

People

  • H. T. Nagamatsu
  • K. H. Cary
  • L. A. Osburg
  • R. E. Sheer Jr.

Organizations

  • General Electric

Tags

Communities of Interest

  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Barium Titanates
  • Boundary Layer
  • Combustion
  • Computational Fluid Dynamics
  • Fluid Dynamics
  • High Pressure
  • High Temperature
  • Ignition Systems
  • Mach Number
  • Measurement
  • Pressure Gages
  • Pressure Measurement
  • Research Facilities
  • Shock Tunnels
  • Spark Plugs
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Computational Modeling and Simulation
  • Electrical Engineering
  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow
  • Space
  • Space - Hall-Effect Thruster