Navier-Stokes Computations of Finned Missiles at Supersonic Speeds

Abstract

The U.S. Army Research Laboratory (ARL) is interested in applying state-of-the-art high performance computing tools to predict the aerodynamics of Army shell at angle of attack for a wide range of Mach number from high subsonic to high supersonic. In this paper, the WIND flow solver has been used to study the aerodynamics of two missile configurations. The GridPro grid generation software has been utilized to generate the computational grids. Several aspects of interest concerning the generation of grids for use with WIND and the process of obtaining solutions is discussed. Comparisons are shown between computation and experiment for several turbulence models.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 2001
Accession Number
ADA394907

Entities

People

  • David J. Haroldsen
  • Walter B. Sturek Sr.

Organizations

  • United States Army Research Laboratory

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamics
  • Boundary Layer
  • Computational Fluid Dynamics
  • Computations
  • Demographic Cohorts
  • Flow
  • Flow Fields
  • Fluid Dynamics
  • Fluid Flow
  • Geometry
  • Graphical User Interface
  • High Performance Computing
  • Mach Number
  • Military Research
  • Parallel Processing
  • Physics Laboratories
  • Turbulence

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Computational Modeling and Simulation
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow