AN AXISYMMETRIC SIMILARITY SOLUTION FOR VISCOUS TRANSONIC NOZZLE FLOW

Abstract

An axisymmetric viscous-transonic equation is presented. A nozzle type similarity solution of this equation has been found, which describes the initial stages in the development of shock-waves downstream of a converging- diverging nozzle throat. This solution is an extension of a two dimensional solution found previously (Sichel 1966). By an appropriate choice of an arbitrary scaling constant solutions were found such that there is essentially a weak normal shock near the axis with effects of wall and shock wave curvature occurring only at a sufficiently large radius. The upstream and downstream asymptotic behavior of these viscous-transonic nozzle solutions has been investigated.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1966
Accession Number
AD0636253

Entities

People

  • M. Sichel
  • Y. K. Yin

Organizations

  • University of Michigan

Tags

Communities of Interest

  • Air Platforms
  • Space

DTIC Thesaurus Topics

  • Axisymmetric
  • Classification
  • Computational Science
  • Contractors
  • Contracts
  • Curvature
  • Department Of Defense
  • Differential Equations
  • Equations
  • Flow
  • Nozzles
  • Security
  • Shock
  • Shock Waves
  • Transonic Nozzles
  • Two Dimensional
  • Waves

Fields of Study

  • Physics

Readers

  • Combustion Dynamics and Shock Wave Physics.
  • Combustion and Flow Dynamics.
  • Linear Algebra