Ducted Rockets.

Abstract

The patent application relates to a method whereby the overall efficiency of a reaction engine having primary and secondary combustion chambers is greatly improved by reducing the primary exhaust velocity to subsonic speed. This is accomplished in a preferred embodiment by using an exhaust tube downstream of the primary nozzle. A tube diameter of about six times that of the primary throat diameter and a tube length of about five to ten times that of the tube diameter is considered optimum.

Document Details

Document Type
Technical Report
Publication Date
Jan 12, 1976
Accession Number
ADD002277

Entities

People

  • Klause C. Schadow

Organizations

  • United States Department of the Navy

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Chambers
  • Chemical Reactions
  • Combustion
  • Combustion Chambers
  • Diameters
  • Ducted Rockets
  • Efficiency
  • Engines
  • Exothermic Reactions
  • Heat Engines
  • Heat Transfer Devices
  • Ignition
  • Internal Combustion Engines
  • Patent Applications
  • Patents
  • Rockets

Readers

  • Fluid Dynamics.
  • Internal Combustion Engine (ICE) Technology.
  • Optical Fiber Sensing and Electromagnetic Propagation.