CALIBRATION OF THE SHOCK TUNNEL COMPONENT OF COUNTERFLOW RANGE (I) AT MACH 7.5

Abstract

Calibration of the shock tunnel component of the Counterflow Range (I) operating with a new nozzle throat designed to yield Mach 7.5 is reported. Transverse pitot-pressure profiles and heat-transfer rates on a hemisphere-cylinder model in the test section were measured at four flow conditions. A single probe was traversed along the nozzle centerline to determine the streamwise pitot-pressure gradient. Shock detachment distances for a hemisphere-cylinder were measured to determine when helium from the shock tunnel driver entered the test section. Results from these tests indicate a repeatable test core of uniform flow having a 12.5-in. diameter. Test times of from 2.5 to 4 msec were recorded before large quantities of helium appeared to be entering the test section. The streamwise pressure measurements indicated a Mach number gradient of 0.2/ft.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1966
Accession Number
AD0632816

Entities

People

  • Henry W. Ball
  • J. H. Haun

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Space

DTIC Thesaurus Topics

  • Abstracts
  • Air Force
  • Boundary Layer
  • Calibration
  • Contracts
  • Free Stream
  • Heat Transfer
  • Hemispheres
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Pressure Gradients
  • Pressure Measurement
  • Shock Tubes
  • Shock Tunnels
  • Tubes
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Fluid Mechanics and Fluid Dynamics.