REALLY HIGH SPEED PROPULSION BY SCRAMJETS

Abstract

The high overall efficiency of the scramjet engine is potentially maintained over the speed range from Mach 5 to 20. At higher speeds, hydrogen fuel is essential and a fixed geometry appears feasible. Optimization of the intake diffusion can be carried out most easily in terms of the intake process efficiency and velocity ratio. The optimum amount of diffusion is reduced when realistic nozzle losses are included. The development of a hypersonic flight test vehicle is recommended.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1965
Accession Number
AD0638520

Entities

People

  • E. T. Curran
  • J. Swithenbank

Organizations

  • University of Sheffield

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Aircrafts
  • Airframes
  • Boundary Layer
  • Combustion
  • Engineering
  • Engines
  • Geometry
  • Heat Energy
  • Heat Transfer
  • Hypersonic Aircraft
  • Hypersonic Vehicles
  • Mach Number
  • Ramjet Engines
  • Supersonic Combustion
  • Supersonic Combustion Ramjet Engines
  • Test Vehicles

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Petroleum Engineering
  • Plasma Physics / Magnetohydrodynamics

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow