Numerical Computation of Base Flow for a Missile in the Presence of a Centered Jet.

Abstract

A thin-layer Navier-Stokes base flow code, developed for projectile aerodynamics, has been used to compute the missile base flow in the presence of a centered propulsive jet. The thin-layer, compressible, Navier-Stokes equations are solved using a time dependent, implicit numerical algorithm. Numerical computations have been made to predict the missile afterbody flow field for both jet-off and jet-on conditions. Solutions are obtained for an axisymmetric cylindrical afterbody where the free stream Mach number is 1.343 and the jet exit Mach number is 2.7. The exhaust jet static pressure is 2.15 times the free stream static pressure. Computed results show both qualitative and quantitative features of the base region flow field.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1984
Accession Number
ADA148784

Entities

People

  • C. J. Nietubicz
  • J. Sahu

Organizations

  • Ballistic Research Laboratory

Tags

Communities of Interest

  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Axisymmetric
  • Base Flow
  • Base Pressure
  • Bodies
  • Boundary Layer
  • Computational Fluid Dynamics
  • Computations
  • Equations
  • Flow
  • Flow Fields
  • Fluid Flow
  • Free Stream
  • Mach Number
  • Navier Stokes Equations
  • Pressure Distribution
  • Projectiles
  • Turbulent Mixing

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Computational Fluid Dynamics (CFD)
  • Fluid Dynamics.