Erosive Burning Studies of Composite Solid Propellants by the Reacting Turbulent Boundary-Layer Approach.

Abstract

The overall objective of the current research is to achieve a basic understanding of the erosive burning mechanism in solid-propellant rocket motors. Both theoretical and experimental studies are undertaken. In the theoretical modeling, a reactive turbulent boundary-layer approach is used to analyze the erosive burning phenomenon. A second-order turbulent closure has been selected in the theoretical formulation. The theoretical model can be used to study the effect of gas velocity, pressure, streamwise pressure gradient, oxidizer particle size, and oxidizer-to-fuel ratio. For model validation, a test rig has been designed to establish a two-dimensional, turbulent boundary layer flow over a flat plate. The test rig can operate under various gas-dynamic conditions. A laser-photodiode servomechanism has been developed to measure the burning rate, and preliminary tests have demonstrated successful operation of the apparatus. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1976
Accession Number
ADA033723

Entities

People

  • Kenneth K. Kuo
  • Mohan K. Razdan

Organizations

  • Pennsylvania State University

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Burning Rate
  • Chemical Reactions
  • Combustion
  • Composite Propellants
  • Computational Fluid Dynamics
  • Energy Transfer
  • Erosive Burning
  • Fluid Dynamics
  • Fluid Mechanics
  • Heat Transfer
  • Ignition
  • Materials Laboratories
  • Materials Processing
  • Propellant Grains
  • Rocket Engines
  • Solid Propellants

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Ocean-Atmosphere Mesoscale Modeling, Data Assimilation, and Flux Boundary Layers
  • Rocket Propulsion.

Technology Areas

  • Directed Energy