THE EFFECT OF THE BOUNDARY LAYER UPON THE FLOW IN A CONICAL HYPERSONIC WIND TUNNEL NOZZLE,

Abstract

Integral equations for the flow in a conical hypersonic nozzle with a thick boundary layer have been formulated and some approximate solutions of these equations have been studied. A method developed by Burke for calculating boundary layer thickness using empirical correlations has been extended to a relatively broad range of stagnation conditions and has been used to compute the effect of boundary layer development upon hypersonic nozzle flow. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1963
Accession Number
AD0412737

Entities

People

  • Martin. Sichel

Organizations

  • University of Michigan

Tags

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Equations
  • Hypersonic Nozzles
  • Hypersonic Wind Tunnels
  • Integral Equations
  • Layers
  • Nozzles
  • Wind Tunnel Nozzles
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow