Numerical Computation of Base Flow for a Projectile at Transonic Speeds

Abstract

The generalized-Axisymmetric Thin-Layer Navier-Stokes computational technique has been modified for projectile base flow analysis. The resulting new numerical capability is used to compute the entire projectile flow field including the recirculatory base flow. Computed results show the qualitative and quantitative details of the overall base flow structure. Base drag is computed for a secant-ogive-cylinder projectile at an angle of attack of zero and compared with available experimental data and a semi-empirical analysis. Results are also presented which show pressure drag, skin friction drag and total aerodynamic drag for Mach No. .9 < M < 1.2.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1983
Accession Number
ADA130293

Entities

People

  • Charles J. Nietubicz
  • Joseph L. Steger
  • Jubaraj Sahu

Organizations

  • Ballistic Research Laboratory

Tags

Communities of Interest

  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Drag
  • Base Pressure
  • Bodies
  • Boundary Layer
  • Computational Fluid Dynamics
  • Computations
  • Difference Equations
  • Equations
  • Flow
  • Flow Fields
  • Fluid Dynamics
  • Fluid Flow
  • Geometry
  • Mach Number
  • Pressure Distribution
  • Skin Friction
  • Turbulent Mixing

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.