A Parametric Study of Ramrocket Performance

Abstract

The performance of a ramrocket having conventional solid propellant is calculated for a range of chosen operating conditions. The geometry of the ramrocket is allowed to vary to suit the flow conditions assumed. Both constant area and constant pressure mixing and combustion are considered. Performance curves in terms of thrust augmentation ratio are presented. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1983
Accession Number
ADA142043

Entities

People

  • Lincoln Erm

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Afterburners
  • Air Breathing
  • Combustion
  • Combustion Chambers
  • Combustion Products
  • Computer Programs
  • Department Of Defense
  • Engineering
  • Equations
  • Exhaust Nozzles
  • Flight Speeds
  • Fluid Mechanics
  • Mach Number
  • Mass Flow
  • Mechanical Engineering
  • Secondary Flow
  • Thrust Augmentation

Fields of Study

  • Physics

Readers

  • Plasma Physics.
  • Rocket Propulsion.
  • Systems Analysis and Design