THE AEROSPACE HYPERSONIC SHOCK TUNNEL

Abstract

The Aerospace Hypersonic Shock Tunnel is described along with an initial calibration at flow Mach numbers of 12, 14, 17, and 18. Room temperature helium is used as the driver gas. Efforts to drive the shock tunnel with com bustion heated helium have been made, and these experiments are also described.

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Document Details

Document Type
Technical Report
Publication Date
Feb 21, 1963
Accession Number
AD0403052

Entities

People

  • Robert L. Varwig

Organizations

  • The Aerospace Corporation

Tags

Communities of Interest

  • Space

DTIC Thesaurus Topics

  • Air Force
  • Barium Titanates
  • Calibration
  • Combustion
  • Gages
  • High Pressure
  • Mach Number
  • Measurement
  • Pressure Gages
  • Pressure Transducers
  • Reynolds Number
  • Shock Tubes
  • Shock Tunnels
  • Shock Waves
  • Tubes
  • United States
  • Waves

Fields of Study

  • Physics

Readers

  • Combustion Dynamics and Shock Wave Physics.
  • Fluid Dynamics.

Technology Areas

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