THE INTERACTION OF A FINITE AMPLITUDE PRESSURE DISTURBANCE WITH A COMBUSTION REGION

Abstract

The method for calculating the interaction of a nonuniform shock with the combustion region at the surface of a burning solid propellant is presented. Interactions were calculated for initial nonuniform shock amplitudes ranging from 2.5 to 150 psi at combustion pressures of 250, 500, and 1000 psia. Results indicated that the amplification of the nonuniform shock by the combustion region decreases with increasing combustion pressure and increasing initial shock amplitude. It was found that the major factor that lead to the amplification of the nonuniform shock was the heat addition in the combustion region. The major attenuating effects were the heat transfer into the propellant, the energy absorbed by the propellant as the shock reflected from its surface, and the steady state velocity gradient in the combustion region.

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1966
Accession Number
AD0482941

Entities

People

  • G. M. Lehmann

Organizations

  • Purdue University

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Burning Rate
  • Chemical Reactions
  • Combustion
  • Combustion Chambers
  • Combustion Products
  • Composite Propellants
  • Computational Fluid Dynamics
  • Difference Equations
  • Differential Equations
  • Equations
  • Heat Transfer
  • Liquid Propellants
  • Physical Properties
  • Physics Laboratories
  • Solid Propellants
  • Thermal Conductivity
  • Transport Properties

Fields of Study

  • Physics

Readers

  • Explosive Engineering.
  • Fluid Dynamics.
  • Rocket Propulsion.