An Evaluation of Nozzle Afterbody Code - AR02P

Abstract

A project was undertaken to develop a computational fluid dynamics (CFD) code for use in nozzle afterbody analysis. Objectives were to create a three-dimensional code capable of calculating afterbody flows with accuracy quantitatively close to the Navier-Stokes solutions, but which would use significantly fewer computer resources. The resulting program coupled an inverse boundary-layer routine with an Euler code and incorporated a jet plume. Calculations were made for the axisymmetric AGARD 15-deg boattail afterbody with variations in nozzle pressure ratio for Mach numbers 0.6 and 0.9, and compared with experimental results. The code predicted drag changes with NPR which showed the proper variations, but the code did not provide the accuracy required for typical nozzle afterbody analysis. (NPR = Nozzle total pressure to free stream static pressure ratio.)

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1986
Accession Number
ADA169743

Entities

People

  • Frederick C. Guyton

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Accuracy
  • Afterbodies
  • Air Force
  • Boattail Afterbodies
  • Bodies
  • Boundaries
  • Boundary Layer
  • Computational Fluid Dynamics
  • Computers
  • Euler Equations
  • Flow Fields
  • Fluid Dynamics
  • Layers
  • Mach Number
  • Pressure Distribution
  • Three Dimensional
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Combustion and Flow Dynamics.
  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)