Analytical Investigation of Multinozzle Plume Flow Fields - Flow Structure and Computation.

Abstract

Progress on the research effort is summarized. Major achievements include (a) the qualitative understanding of the complex shock structure impingement of two underexpanded rocket plumes and (b) the development of three dimensional computational techniques. A three dimensional isentropic inviscid supersonic computer code is operational and the core flow field of rectangular nozzles has been computed. Advanced techniques built around floating discrete discontinuity surfaces and singularity cells are being incorporated into this program for the computation of the impingement of two rectangular plumes.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1976
Accession Number
ADA034017

Entities

People

  • Stanley Rudman

Organizations

  • Grumman

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Air Force
  • Computational Fluid Dynamics
  • Computations
  • Differential Equations
  • Equations
  • Flow
  • Flow Fields
  • Fluid Dynamics
  • Fluid Mechanics
  • Geometry
  • Partial Differential Equations
  • Shock Waves
  • Supersonic Flow
  • Three Dimensional
  • Three Dimensional Flow
  • Two Dimensional
  • United States Government

Readers

  • Combustion and Flow Dynamics.
  • Fluid Dynamics.
  • Technical Research and Report Writing.

Technology Areas

  • Hypersonics