An Investigation into the Performance Characteristics of a Solid Fuel SCRAMJET Propulsion Device

Abstract

An investigation was conducted to evaluate the performance qualities of a supersonic ramjet propulsion device (SCRAMJET) using a solid fuel. The fuel grains were fabricated from Plexiglas and were cylindrical, with an axisymmetric, circular perforation that diverged in the downstream direction. A small amount of hydrogen gas was required in an initial recirculation zone in order to sustain combustion. With Combustor inlet conditions of 150 psia, 1000 R, and a Mach number of 1.5, a combustor exit Mach number of approximately 1.4 was maintained. Due to poor mixing conditions, the combustion efficiency of the solid fuel only 57%.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1991
Accession Number
ADA246486

Entities

People

  • William J. Angus

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Acquisition
  • Combustion
  • Combustion Products
  • Combustors
  • Data Acquisition
  • Efficiency
  • Fuels
  • Ignition
  • Mach Number
  • Propulsion Systems
  • Solid Fuels
  • Stagnation Pressure
  • Stagnation Temperature
  • Static Pressure
  • Supersonic Combustion
  • Supersonic Combustion Ramjet Engines
  • Test Facilities

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Electrochemical Engineering/ Fuel Cell Technologies
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow