Laminar Flow-Field Computation in Axisymmetric Nozzles.

Abstract

A numerical procedure for computing the laminar flow-field in nozzles at throat Reynolds numbers of 300-3000 is described. Such nozzles are found in spacecraft position control thrusters, chemical lasers, and low density hypersonic wind-tunnels. A parabolic approximation of the Navier-Stokes equations (the boundary layer equations) is transformed to Von Mises form and solved numerically by a central difference method. The entire subsonic and supersonic flow-field is computed. No assumptions or approximations, other than those inherent in the flow equations, are involved. The method is of the direct type and the flow-field for any given nozzle geometry may, in principle, be computed. Examples are given comparing computed results with published experimental data. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1977
Accession Number
ADA055124

Entities

People

  • B. C. Barber

Organizations

  • Royal Aircraft Establishment

Tags

Communities of Interest

  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Chemical Lasers
  • Difference Equations
  • Differential Equations
  • Equations
  • Flow Fields
  • Flow Rate
  • Fluid Dynamics
  • Geometry
  • Heat Transfer
  • Laminar Flow
  • Low Density
  • Mach Number
  • Mass Flow
  • Pressure Gradients
  • Reynolds Number
  • Static Pressure

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Directed Energy
  • Hypersonics
  • Hypersonics - Hypersonic Flight
  • Hypersonics - Hypersonic Flow
  • Space
  • Space - Hall-Effect Thruster