Application of CFD to High Angle of Attack Missile Flow Fields

Abstract

Computational fluid dynamics (CFD) calculations have been performed for a missile body with and without fins. Numerical flow field computations have been made for various Mach numbers and roll angles using an unsteady zonal Navier-Stokes code (ZNSFLOW) and the chimera composite grid discretization technique at supersonic velocity and high angle of attack. Steady-state numerical results have been obtained and compared for cases modeling an ogive-cylinder missile with and without fins. Computed results show the details of the expected flow field features to include vortical crossflow separation. Computed results are compared with experimental data obtained for the same configurations and conditions and are generally found to be in good agreement with the data. The results help to show the predictive capabilities of CFD techniques for supersonic projectiles at incidence.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 2000
Accession Number
ADA384925

Entities

People

  • Jubaraj Sahu
  • Karen Heavey
  • Surya Dinavahi

Organizations

  • United States Army Research Laboratory

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aerodynamic Forces
  • Astronautics
  • Boundaries
  • Coefficients
  • Computational Fluid Dynamics
  • Computational Science
  • Equations
  • Experimental Data
  • Fluid Dynamics
  • Fluid Flow
  • High Angles
  • Information Transfer
  • Mechanics
  • Surfaces
  • Three Dimensional
  • United States

Fields of Study

  • Physics

Readers

  • Computational Fluid Dynamics (CFD)
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow