Numerical Simulation of Axisymmetric Base Flow on Tactical Missiles with Propulsive Jet

Abstract

The axisymmetric Lockheed Viscous Implicit Solver (LVIS) Navier- Stokes computer code is modified to incorporate the capability for computing the flow in the base region of a tactical missile with propulsive jet. Modifications include generalization of the computational space to accommodate the geometry of the base and implementation of two turbulence models of the two-equation type (l-epsilon and k-W). Computer runs are made with both turbulence models. The results of these computations are similar, but some differences are observed in the recirculating near-wake flow and in the shear layers that separate it from the high-speed streams of the propulsive jet and of the external flow. These differences are attributed to the greater eddy viscosity predicted by the k- epsilon model.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1987
Accession Number
ADA196169

Entities

People

  • P. D. Thomas
  • R. J. Conti
  • R. P. Reklis
  • R. R. Roloff

Organizations

  • Lockheed Martin Missiles and Space

Tags

Communities of Interest

  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Computational Fluid Dynamics
  • Computational Science
  • Computations
  • Computer Programs
  • Computers
  • Difference Equations
  • Differential Equations
  • Equations
  • Euler Equations
  • Fluid Dynamics
  • Fluid Flow
  • Mechanical Properties
  • Navier Stokes Equations
  • Reynolds Number
  • Turbulent Mixing
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Computational Fluid Dynamics (CFD)
  • Fluid Mechanics and Fluid Dynamics.
  • Military Training and Readiness Simulation

Technology Areas

  • Space
  • Space - Hall-Effect Thruster