Accession Number:

ADA454590

Title:

Numerical Simulation of a Thrust Augmented Rocket Nozzle

Descriptive Note:

Technical Paper Preprint

Corporate Author:

AEROJET SACRAMENTO CA

Report Date:

2006-05-30

Pagination or Media Count:

11.0

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.

Subject Categories:

  • Fluid Mechanics
  • Combustion and Ignition

Distribution Statement:

APPROVED FOR PUBLIC RELEASE