The Use of Stream Thrust Concepts for the Approximate Evaluation of Hypersonic Ramjet Engine Performance

Abstract

A simplified method of estimating the performance of supersonic combustion ramjet engines is presented. The method utilizes stream thrust concepts and enables valid performance estimates to be made without the aid of a computer program; only a few simple graphs are required. A new "reference" stream thrust quantity is defined and shown to be of value in estimating engine flight performance. The data given in this report enable performance estimates to be made for hydrogen fueled engines operating stoichiometrically for speeds in excess of about Mach 8.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1973
Accession Number
AD0769481

Entities

People

  • Edward T. Curran
  • Roger R. Craig

Organizations

  • Air Force Research Laboratory

Tags

Communities of Interest

  • Materials and Manufacturing Processes
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Air Force Facilities
  • Combustion
  • Combustors
  • Computer Programs
  • Computers
  • Engines
  • Exits
  • Flight Speeds
  • Fuel Injection
  • Hydrogen
  • Mass Flow
  • Measurement
  • Ramjet Engines
  • Supersonic Combustion
  • Supersonic Combustion Ramjet Engines
  • Supersonic Flow

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Combustion science or combustion engineering.
  • Statistical inference.

Technology Areas

  • Hypersonics