A SHOCK TUBE FOR PRODUCING SUBSONIC, TRANSONIC, AND SUPERSONIC FLOWS FOR AERODYNAMIC TESTING

Abstract

A shock tube is proposed in which the flow conditions between the shock wave and advancing interface are expected to range from low subsonic to moderate supersonic speeds. Furthermore, testing times of 10 msec or more are predicted, a time quite adequate for aerodynamic force measurements. The driven section in the proposed facility is large enough to accommodate large scale models. To test the feasibility of the proposed tube, a shock tube was assembled using a surplus 7-foot diameter vacuum tank as a driven section and 12-in. flanged pipe for the driver. A series of tests were performed to determine shock formation time and experimental testing time. The results of thest tests are reported.

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Document Details

Document Type
Technical Report
Publication Date
Feb 18, 1963
Accession Number
AD0403045

Entities

People

  • R. L. Varwig

Organizations

  • The Aerospace Corporation

Tags

Communities of Interest

  • Ground and Sea Platforms

DTIC Thesaurus Topics

  • Air Force
  • Blunt Bodies
  • Bodies
  • Flow
  • Fluid Flow
  • Mach Number
  • Measurement
  • Research Facilities
  • Shock Tubes
  • Shock Tunnels
  • Shock Waves
  • Test And Evaluation
  • Test Facilities
  • Tubes
  • United States
  • Waves
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Combustion Dynamics and Shock Wave Physics.
  • Electrical Engineering

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow