The Problem of Determining the Optimum Critical Operating Parameters for a Nonisobaric Motor with Divergent Nozzle

Abstract

A solution is given to the problem of nonsteady state operation of a liquid rocket motor, using the dynamical differential equations of turbulent flow. The solutions are used to determine the optimum and critical parameters, together with the stability limits, on the basis of a nonisobaric motor model. The determination of these parameters makes it possible to correct the design method used for rocket motors.

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Document Details

Document Type
Technical Report
Publication Date
Aug 04, 1964
Accession Number
AD0603947

Entities

People

  • Robert Staniszewski

Organizations

  • Air Force Systems Command

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Chambers
  • Coefficients
  • Combustion
  • Combustion Chambers
  • Computational Fluid Dynamics
  • Differential Equations
  • Equations
  • Flow Rate
  • Fluid Dynamics
  • Fluid Flow
  • Heat Energy
  • Ignition Lag
  • Propulsion Systems
  • Rocket Engines
  • Rocket Propulsion
  • Specific Gravity
  • Transfer Functions

Fields of Study

  • Physics

Readers

  • Combustion science or combustion engineering.
  • Control Systems Engineering.