A Method of Determining the Turbulent Base Pressure in Uniform and Non-Uniform Supersonic Axisymmetric Flows.

Abstract

This report describes the base pressure computation procedure and computer program developed at the University of Notre Dame. The computation is valid for supersonic high Reynolds number flow at zero yaw. The computation is started upstream of the afterbody by means of the Method of Characteristics; hence, the effect of boattail, or flare, angle is determined. The effect of forebody shape can be indirectly determined if the external non-uniform Mach number profile is used as input for the start of the characteristics solution. However, the assumption of a uniform external flow generally provides good results. Examples are shown for uniform external flow inputs and for realistic non-uniform initial conditions. Also, results showing the effects of afterbody angle are presented. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1981
Accession Number
ADA107318

Entities

People

  • Lyle D. Kayser
  • Thomas J. Mueller

Organizations

  • Ballistic Research Laboratory

Tags

Communities of Interest

  • Energy and Power Technologies
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Afterbodies
  • Axisymmetric
  • Axisymmetric Flow
  • Base Pressure
  • Bodies
  • Boundary Layer
  • Computational Fluid Dynamics
  • Computer Programs
  • Computers
  • Cylindrical Bodies
  • Flow Fields
  • Fluid Dynamics
  • Geometry
  • Grids
  • Mach Number
  • Method Of Characteristics
  • Procedures (Computers)

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow