Three Dimensional Base Flow Calculation for a Projectile at Transonic Velocity

Abstract

As part of an ongoing research program to develop predictive capabilities for projectile aerodynamics at transonic speeds, a three dimensional base flow code has been developed to compute the base region or wake flow behind the projectile. The time-marching, thin-layer, Navier-Stokes computational technique has been used, in conjunction with a unique flow field segmentation procedure, to compute the full flow field over a projectile including the base region at angle of attack. A flow field solution has been obtained for a typical artillery projectile at Mach number, M = .96 and 4 deg angle of attack. Details of the flow field on the boattailed afterbody and in the base region are presented. Surface pressure, base pressure and aerodynamic coefficients are computed and compared with experiment.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1987
Accession Number
ADA184171

Entities

People

  • Jubaraj Sahu

Organizations

  • Ballistic Research Laboratory

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Base Flow
  • Base Pressure
  • Bodies
  • Boundary Layer
  • Computational Fluid Dynamics
  • Computations
  • Equations
  • Experimental Data
  • Fluid Dynamics
  • Fluid Flow
  • Geometry
  • Mach Number
  • Navier Stokes Equations
  • Pressure Distribution
  • Three Dimensional
  • Turbulent Mixing
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.
  • ballistics.