Numerical Solution of a Supersonic Nozzle Afterbody Flow with Jet Exhaust

Abstract

Numerical solutions to the compressible turbulent Navier-Stokes equations for supersonic flow at Mach number 1.5, past an axisymmetric nozzle boattail with jet exhaust were obtained using MacCormack's explicit numerical scheme. The AGARD 10 deg.-nozzle was considered and a total of five cases were computed showing the effects of boattail geometry, jet-exhaust temperature, boattail wall temperature and the differences with the corresponding two- dimensional case. It was established that the hot boattail surface reduces the pressure drag significantly as does the hot jet exhaust when compared with the cold wall, cold exhaust case. The present approach can be used directly for boattailing nozzles for minimum pressure drag, as well as for a parametric study for aircraft designers.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1979
Accession Number
ADA076116

Entities

People

  • Ameer G. Mikhail

Organizations

  • University of Dayton

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Computational Fluid Dynamics
  • Dynamics
  • Equations
  • Fluid Dynamics
  • Fluid Flow
  • Geometry
  • Mach Number
  • Navier Stokes Equations
  • Physics Laboratories
  • Reynolds Number
  • Supersonic Flow
  • Three Dimensional
  • Turbulent Flow
  • Turbulent Mixing
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Combustion and Flow Dynamics.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow