Navier-Stokes Computations of Transonic Flow Over a Projectile with a Two-Equation Model of Turbulence,

Abstract

A thin-layer Navier-Stokes code has been used to compute the axisymmetric turbulent flow over a projectile at transonic speeds. The thin layer form of the compressible Navier-Stokes equations is solved using a time dependent, implicit numerical algorithm. Numerical computations have been made using aero-equation (algebraic) and two-equation (kinetic energy and length scale) turbulence eddy viscosity models. The algorithm, and how the turbulence models are incorporated into it, are described. Computed results have been obtained for a secant-ogive-cylinder-boattail shape at M infinity = .94 and .97 using both models and are compared with experiment. (Author)

Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1984
Accession Number
ADP004797

Entities

People

  • J. E. Danberg
  • J. Sahu

Organizations

  • Ballistic Research Laboratory

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Algorithms
  • Computational Fluid Dynamics
  • Computations
  • Equations
  • Flow
  • Flow Fields
  • Fluid Dynamics
  • Fluid Flow
  • Kinetic Energy
  • Mathematical Analysis
  • Navier Stokes Equations
  • Projectiles
  • Transonic Flow
  • Turbulence
  • Turbulent Flow

Fields of Study

  • Physics

Readers

  • Computational Fluid Dynamics (CFD)
  • Fluid Dynamics.