Computational Fluid Dynamics Modeling of Submunition Separation from Missile

Abstract

Computational fluid dynamics calculations have been performed for a multi-body system consisting of a main missile and a number of submunitions. Numerical flow field computations have been made for various orientations and locations of submunitions using an unsteady, zonal Navier-Stokes code and the chimera composite grid discretization technique at low supersonic speeds and 0 deg angle of attack. Steady state numerical results have been obtained and compared for cases modeling six submunitions in pitch-plane symmetry and ten submunitions for which symmetry could not be exploited. Computed results show the details of the expected flow field features including the shock interactions. Computed results are compared with limited experimental data obtained for the same configuration and conditions and are generally found to be in good agreement with the data. The results help to quantify changes in the aerodynamic forces and moments, which are attributable to changes in position of the submunitions relative to one another.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
May 01, 1999
Accession Number
ADA364736

Entities

People

  • Harris L. Edge
  • Jubaraj Sahu
  • Karen R. Heavey

Organizations

  • United States Army Research Laboratory

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Abstracts
  • Aerodynamic Forces
  • Boundary Layer
  • Computational Fluid Dynamics
  • Computations
  • Equations
  • Experimental Data
  • Flow Fields
  • Fluid Dynamics
  • Geometry
  • Layers
  • Military Research
  • Molecular Dynamics
  • Pressure Measurement
  • Short Range Ballistic Missiles
  • Steady State
  • Three Dimensional

Fields of Study

  • Physics

Readers

  • Computational Fluid Dynamics (CFD)
  • Fluid Dynamics.
  • Munitions and Ordnance Engineering

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow