The Gasdynamics of Self-Regulation of a Supersonic Plug Nozzle

Abstract

Experimental studies are presented of supersonic plug nozzles. The purpose of the study was to determine the nozzle performance at characteristic pressure ratios and to formulate a gasdynamic theory for variable nozzles. Cold air at 6 kg/cm (superscript 2) and 345 degrees K was used as the working medium. The static pressure was measured along the nozzle, the plug, and the nozzle inlet. In addition, the shadow method was used to visually examine the exhaust jet. Changes in the pressure ratio in the nozzle were determined from pressure variations at the inlet cross-section of the nozzle. The study included plug nozzles with single and multiple combustion chambers. In addition to rocket application, plug nozzles have potential application in turbojet and ramjet engines.

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Document Details

Document Type
Technical Report
Publication Date
Mar 19, 1969
Accession Number
AD0861453

Entities

People

  • Tadeusz Gajewski

Organizations

  • Air Force Systems Command

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Barometric Pressure
  • Chambers
  • Combustion
  • Combustion Chambers
  • Combustion Products
  • Engine Components
  • Fluid Flow
  • Jet Engines
  • Laval Nozzles
  • Plug Nozzles
  • Pressure Distribution
  • Regulations
  • Rocket Engines
  • Shock Waves
  • Static Pressure
  • Supersonic Nozzles
  • Turbojet Engines

Fields of Study

  • Physics

Readers

  • Explosive Engineering.
  • Fluid Dynamics.
  • Internal Combustion Engine (ICE) Technology.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow