Radiative heat feedback in aluminized solid propellant combustion

M. Quinn Brewster, David L. Parry

Research output: Contribution to journalArticle

Abstract

A one-dimensional model has been developed to describe the combustion, flow, and radiant transport processes by aluminum and alumina particles near the surface of a burning aluminized composite solid propellant. The equations of mass, momentum, and energy have been solved to obtain the species concentration, velocity, and temperature profiles near the propellant surface. The decoupled radiative transfer equation has also been solved using the two-flux model to obtain the radiant flux profiles and the radiative heat feedback to the propellant surface. The results of the model indicate that the radiant heat feedback to the surface of a typical aluminized composite propellant would be 300-400 W/cm2 or about 20% of the total energy flux required to heat the solid propellant to the surface temperature.

Original languageEnglish (US)
Pages (from-to)123-130
Number of pages8
JournalJournal of thermophysics and heat transfer
Volume2
Issue number2
DOIs
StatePublished - Apr 1988

ASJC Scopus subject areas

  • Condensed Matter Physics
  • Aerospace Engineering
  • Mechanical Engineering
  • Fluid Flow and Transfer Processes
  • Space and Planetary Science

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