A Computer Code for Fully Coupled, Two-Phase Rocket Nozzle Flows.

Abstract

This report describes the development of a unified rocket nozzle computer program that is intended to serve as an aid in the study of the physical and chemical processes that control rocket exhaust plume dynamics, including plume visibility. The computer program is composed of the transonic, two-phase code of Kliegel and Nickerson and the AeroChemFULLNOZ nozzle code. This combination allows chamber conditions to be used to initiate a continuous nozzle calculation, thus eliminating the assumptions of supersonic start line gas and particle properties previously required by FULLNOZ. Sample calculations are presented for a small, conical nozzle motor burning a low smoke propellant. These calculations describe the sensitivity of the unified code to variations in start line conditions, particle sizes, mass loading, and particle drag and heat transfer coefficients. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1978
Accession Number
ADA052746

Entities

People

  • Roger D. Thorpe

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Chemical Kinetics
  • Chemical Reactions
  • Computer Programs
  • Energy Transfer
  • Equations
  • Exhaust Plumes
  • Gas Turbine Nozzles
  • Geometry
  • Heat Transfer
  • Heat Transfer Coefficients
  • Particle Size
  • Payload
  • Rocket Engines
  • Rocket Exhaust
  • Solid Propellants

Fields of Study

  • Physics

Readers

  • Aerosol Science/Aerosol Physics
  • Combustion and Flow Dynamics.
  • Computer Science.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flight