Effect of Injector Design on External Burning of Solid Propellants in Mach 2 Airstream.

Abstract

Injector concepts and propellant formulations were evaluated under simulated external burning conditions in a planar, two-dimensional wind tunnel. The ratio of base pressure rise to propellant mass flow was significantly improved by reduction of the injection velocity from supersonic to subsonic speed, the use of a downstream-facing step upstream of the supersonic and subsonic injector, and the use of magnesium loaded propellants.

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1977
Accession Number
ADA035451

Entities

People

  • Don J. Chieze
  • Klaus C. Schadow

Organizations

  • Naval Air Weapons Station China Lake

Tags

DTIC Thesaurus Topics

  • Base Pressure
  • Combustion
  • External Burning
  • Flow
  • Injectors
  • Magnesium
  • Mass
  • Mass Flow
  • Physical Properties
  • Propellants
  • Solid Propellants
  • Two Dimensional
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Fluid Mechanics and Fluid Dynamics.
  • Rocket Propulsion.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow