DESCRIPTION OF THE 120-INCH HYPERSONIC SHOCK TUNNEL AND ANTICIPATED PERFORMANCE

Abstract

A 120-inch hypersonic shock tunnel has been installed in the Air Force Aero Propulsion Laboratory to provide a capability for testing advanced ramjet engine components and large-scale propulsion systems. The shock tunnel utilizes driver gases that are unheated; presently, either hydrogen or helium, pressurized to 30,000 psia, is used as the driver gas. The 'Tailored' interface technique is used to allow for maximum testing time. The facility in its present configuration yields test Mach numbers in the range 18 to 35. Modifications are being made to extend this range to approximately Mach 8 to 10.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1966
Accession Number
AD0632234

Entities

People

  • Harold F. Chambers
  • Philippe O. Bouchard

Organizations

  • Air Force Research Laboratory

Tags

Communities of Interest

  • Air Platforms
  • Human Systems
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Engine Components
  • Engines
  • Films
  • Governments
  • Heat Transfer
  • High Pressure
  • Hydrogen
  • Mach Number
  • Propulsion Systems
  • Ramjet Engines
  • Shock Tubes
  • Shock Tunnels
  • Supersonic Combustion Ramjet Engines
  • Test Facilities
  • Tubes
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Systems Analysis and Design

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow