An Analysis of External Burning Propulsion.

Abstract

A computer model of external burning propulsion of axisymmetric, supersonic vehicles is described. Reactive gaseous injectant issues from individual nozzles around the vehicle periphery, near the base. At the base these individual jets merge into an annulus of injectant surrounding the base cavity. Detailed individual-jet calculations in the region upstream of the base are made by an existing analysis developed for fuel-rich jet interaction. The injectant annulus is calculated assuming an adjustable fraction of the flow at equilibrium and the remainder frozen; mass and momentum are conserved, and the transverse pressure gradients are assumed negligible. Results and trends are presented for parameters including Mach number, altitude, vehicle geometry and injectant mass and momentum flux and composition. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1979
Accession Number
ADA074639

Entities

People

  • D. W. Harvey

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Altitude
  • Base Pressure
  • Boundaries
  • Chemical Reactions
  • Chemistry
  • Combustion
  • Computational Fluid Dynamics
  • Computer Programs
  • Equations
  • External Burning
  • Flow Rate
  • Fluid Dynamics
  • Geometry
  • Mach Number
  • Pressure Gradients
  • Solid Propellants
  • Turbulent Mixing

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Combustion science or combustion engineering.
  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flight