Computation of Axisymmetric Separated Nozzle-Afterbody Flow

Abstract

The development of a computer program for solving the compressible, axisymmetric, mass-averaged Navier-Stokes equations is described. The basic numerical algorithm is the MacCormack explicit predictor-corrector scheme. Turbulence modeling is accomplished using an algebraic, two-layer eddy viscosity model with a novel modification dependent on the streamwise gradient of vorticity. Comparisons of computed results with experimental data are presented for several nozzle-afterbody configurations with either or simulated plumes.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1980
Accession Number
ADA079694

Entities

People

  • J. L. Jacocks

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Computational Fluid Dynamics
  • Computer Programs
  • Computers
  • Engineering
  • Equations
  • Flow Fields
  • Fluid Dynamics
  • Fluid Flow
  • Geometry
  • Measurement
  • Navier Stokes Equations
  • Pressure Distribution
  • Simulators
  • Tennessee
  • United States

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)
  • Fluid Dynamics.