An Experimental Investigation of the Dual Chamber Rocket Motor

Abstract

An experimental investigation was conducted to further determine the operating characteristics of the dual chamber rocket motor. Axisymmetric and two-dimensional apparatuses were used with air flow to simulate the actual flow. Without special design considerations the sustainer exhaust was found to always shockdown within the booster cavity except for very short booster lengths. Thrust was found to be insensitive to booster cavity length. With nozzle throat area ratios and booster diameters sized properly supersonic flow could be maintained within the booster cavity. Practical designs for actual motors appear quite feasible, especially for a nozzleless booster.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1980
Accession Number
ADA092135

Entities

People

  • D. W. Netzer
  • J. E. Beakley
  • J. F. Mcfillin Jr.
  • S. T. Van Brocklin

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Flow
  • Air Force
  • Blast Tubes
  • Booster Rocket Engines
  • Diameters
  • Flow
  • Flow Rate
  • Flow Visualization
  • Geometry
  • Plastic Explosives
  • Rocket Engines
  • Rocket Propulsion
  • Rockets
  • Stagnation Pressure
  • Static Pressure
  • Supersonic Flow
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Fluid Mechanics and Fluid Dynamics.
  • Rocket Propulsion.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow