THEORETICAL PERFORMANCE OF SELECTED FLUID INJECTANTS FOR THRUST VECTOR CONTROL

Abstract

A linearized model of fluid injection thrust vector control is developed and shown to be in good agreement with experimental data. It is used to predict performance of various fluid injectants (gas and liquid; inert and reactive) in conjunction with a hypothetical rocket. The results are discussed in detail.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1962
Accession Number
AD0406683

Entities

People

  • M. Shandor
  • R. E. Walker

Organizations

  • Johns Hopkins University

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Chemical Reactions
  • Dissociation
  • Enthalpy
  • Exhaust Gases
  • Flow Rate
  • Gas Turbine Nozzles
  • Gases
  • Liquids
  • Mach Number
  • Nozzles
  • Physics
  • Physics Laboratories
  • Rocket Engines
  • Rocket Nozzles
  • Supersonic Flow
  • Three Dimensional
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Computational Modeling and Simulation
  • Fluid Dynamics.