Numerical Computations of Supersonic Flow Over a Square Cross-Section Missile

Abstract

This report describes a computational study undertaken to determine the aerodynamics of a nonaxisymmetric missile with a square cross section. Numerical solutions have been obtained at supersonic speeds for various roll orientations and angles of attack using a two-equation Reynolds-averaged Navier-Stokes turbulence model. Numerical results show the qualitative features (vortices and cross-flow separation regions) of the flow field at various stream wise positions along the missile configurations. Aerodynamic coefficients have been obtained from the computed solutions and found to match well with the available experimental data for these configurations. These numerical results show the ability of computational fluid dynamics techniques to accurately predict the aerodynamics of nonaxisymmetric missiles with a square cross section.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 2005
Accession Number
ADA439496

Entities

People

  • Jubaraj Sahu
  • Sidra I. Silton

Organizations

  • United States Army Research Laboratory

Tags

DTIC Thesaurus Topics

  • Aerodynamics
  • Boundary Layer
  • Computational Fluid Dynamics
  • Computations
  • Cross Flow
  • Equations
  • Experimental Data
  • Flow
  • Flow Fields
  • Flow Separation
  • Fluid Dynamics
  • Fluid Flow
  • Geometry
  • Orientation (Direction)
  • Pressure Distribution
  • Supersonic Flow
  • Three Dimensional

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Computational Fluid Dynamics (CFD)

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow