Investigation of the Effect of Low Thrust Levels on the Base Pressure of a Cylindrical Body at Supersonic Speeds

Abstract

Results of supersonic wind tunnel tests are presented which show the effects of varying nozzle geometry, location, and supply pressure on the base pressure of a cylindrical body at zero angle of attack. The purpose of the tests was to investigate the parametric influences in the regions where base pressure is near a minimum, which occurs in the lower range of thrust levels. A bibliography of related experimental results is also included.

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Document Details

Document Type
Technical Report
Publication Date
May 07, 1970
Accession Number
AD0871913

Entities

People

  • C. E. Brazzel
  • T. A. Martin

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Supplies
  • Base Pressure
  • Bodies
  • Conical Nozzles
  • Cylindrical Bodies
  • Free Stream
  • Geometry
  • Government (Foreign)
  • Guided Missiles
  • Mach Number
  • Nozzles
  • Pressure Distribution
  • Reynolds Number
  • Static Pressure
  • Supersonic Wind Tunnels
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Control Systems Engineering.
  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow