High Mach Number Turbulent Boundary Layer with and without Favorable Pressure Gradient.

Abstract

Boundary layer profiles of total temperature and total pressure, together with surface pressure and heat transfer rates, in turbulent boundary layers with and without favorable pressure gradients have been measured with a Mach 6 wind tunnel facility. Experimental results were correlated and comparisons between the cases with and without favorable pressure gradient were made. Effects of pressure gradient and upstream history to the boundary layer development were investigated. Numerical results of an existing turbulent boundary layer theory were also compared with present experiments.

Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1975
Accession Number
ADA014730

Entities

Organizations

  • New York University

Tags

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Heat Transfer
  • Layers
  • Mach Number
  • Pressure Gradients
  • Test Facilities
  • Turbulent Boundary Layer
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.