Heat Transfer Modelling of Thrust Vector Control Systems

Abstract

This thesis presents a model of heat transfer phenomenon in thrust vector control systems, using the PHOENICS computer code. To simplify the problem of heat transfer to solid objects in rocket exhaust, simple wedge bodies have been examined in supersonic gas flow for both turbulent and laminar flow cases. The study gives an estimate of skin friction coefficient, surface heat flux, heat transfer coefficient, Stanton number distributions, and computer run times.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1986
Accession Number
ADA167933

Entities

People

  • Alp Yukselen

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • Energy and Power Technologies
  • Space

DTIC Thesaurus Topics

  • Boundary Layer
  • Computational Fluid Dynamics
  • Computational Science
  • Control Systems
  • Differential Equations
  • Energy
  • Flow Fields
  • Fluid Flow
  • Gas Flow
  • Geometry
  • Heat Transfer
  • Heat Transfer Coefficients
  • Mach Number
  • Mechanical Engineering
  • Pressure Distribution
  • Skin Friction
  • Thrust Vector Control Systems

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Computational Modeling and Simulation

Technology Areas

  • Hypersonics