Supersonic Flow Over Cylindrical Afterbodies with Base Bleed.

Abstract

Computations of supersonic flow over two cylindrical afterbodies have been made using a thin-layer Navier-Stokes base flow code. The capability to compute the base flow with base bleed at supersonic speeds has been developed and used to show the effect of mass injection on the base pressure or base drag. Solutions have been obtained for a projectile and a missile configuration having cylindrical afterbodies. Numerical results show the effect of base bleed on the near wake flow field. The rise in base pressure or reduction in base drag has been clearly predicted for various mass injection rates and comparison with experimental data shows generally good agreement.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1986
Accession Number
ADA171461

Entities

People

  • Jubaraj Sahu

Organizations

  • Ballistic Research Laboratory

Tags

Communities of Interest

  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Base Flow
  • Base Pressure
  • Boundary Layer
  • Combustion
  • Computational Fluid Dynamics
  • Computations
  • Experimental Data
  • Flow Fields
  • Flow Rate
  • Fluid Dynamics
  • Fluid Flow
  • Mach Number
  • Mass Flow
  • Measurement
  • Pressure Distribution
  • Supersonic Flow
  • Turbulent Mixing

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow