One- and Two-Phase Nozzle Flows.

Abstract

A time-dependent technique, in conjunction with the boundary-fitted coordinates system, is applied to solve a gas-only one-phase flow and a fully-coupled, gas-particle two-phase flow inside nozzles with small throat radii of curvature, steep wall gradients, and submerged configurations. The emphasis of the study has been placed on one- and two-phase flow in the transonic region. Various particle size and particle mass fractions have been investigated in the two-phase flow. The salient features associated with the two-phase nozzle flow compared with those of the one-phase flow are illustrated through the calculations for a JPL nozzle configuration, for the Titan III solid rocket motor nozzle, and for the submerged nozzle configuration utilized in the Inertial Upper Stage (IUS) solid rocket motor. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Jan 31, 1980
Accession Number
ADA085806

Entities

People

  • I-shih Chang

Organizations

  • The Aerospace Corporation

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Combustion
  • Combustion Products
  • Differential Equations
  • Energy
  • Energy Transfer
  • Engineering
  • Equations
  • Flow Fields
  • Fluid Dynamics
  • Gas Flow
  • Geometry
  • Heat Transfer
  • Mach Number
  • Particle Size
  • Payload
  • Pressure Distribution
  • Rocket Engines

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Computational Fluid Dynamics (CFD)
  • Rocket Propulsion.