AN EXPERIMENTAL INVESTIGATION OF HEAT TRANSFER AND PRESSURE EFFECTS ON LONGITUDINAL COMBUSTION INSTABILITY IN A ROCKET MOTOR USING PREMIXED GASEOUS PROPELLANTS

Abstract

Several experiments were performed to further investigate the high frequency, longitudinal, combustion instability regions and their limits encountered during operation of a rocket motor using gaseous propellants. These experiments were designed to change the heat transfer rate to the injector face by changing heat transfer properties of the propellant gases and injector configuration; to measure the axial temperature profile in the combustion region; to study the effects of changing the mean chamber pressure; and to measure the wave form of the oscillatory pressure in the combustion chamber.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1963
Accession Number
AD0407931

Entities

People

  • Walter J. Schob Jr.

Organizations

  • Princeton University

Tags

DTIC Thesaurus Topics

  • Accuracy
  • Air Force
  • Combustion
  • Combustion Chambers
  • Combustion Products
  • Frequency
  • Heat Transfer
  • Heat Transfer Coefficients
  • Pressure Measurement
  • Pressure Transducers
  • Propellants
  • Rocket Engines
  • Rockets
  • Shock Waves
  • Transport Properties
  • Waveforms
  • Waves

Fields of Study

  • Physics

Readers

  • Combustion science or combustion engineering.
  • Fluid Dynamics.