Numerical Simulation of a Thrust Augmented Rocket Nozzle

Abstract

Numerical results are presented from a reacting-flow Navier-Stokes simulation of a rocket nozzle in which fuel is injected downstream of the nozzle throat for the purposes of augmenting the thrust. The numerical results are compared with experimental data in terms of overall thrust and specific impulse as well as pressure distribution along the nozzle wall. The flow physics associated with the thrust augmentation is also described. The investigation shows that propellant injection downstream of the throat is a viable method for augmenting rocket thrust. In addition, the augmented thrust levels increase with increasing levels of injected mass flow. Finally, the investigation shows that the numerical predictions are in good agreement with the experimental results.

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Document Details

Document Type
Technical Report
Publication Date
May 30, 2006
Accession Number
ADA454590

Entities

People

  • Clement Yam
  • Melvin J. Bulman
  • Roger L. Davis

Organizations

  • Aerojet Rocketdyne Holdings

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force Research Laboratories
  • Combustion
  • Combustion Products
  • Computational Fluid Dynamics
  • Experimental Data
  • Flow
  • Fluid Dynamics
  • Gas Turbine Nozzles
  • Gas Turbines
  • Mass Flow
  • Pressure Distribution
  • Rocket Engines
  • Rocket Nozzles
  • Specific Impulse
  • Three Dimensional
  • Thrust Augmentation
  • Turbines

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Computational Fluid Dynamics (CFD)