BOUNDARY LAYER SEPARATION IN THE PRESENCE OF HEAT TRANSFER

Abstract

Effects of heat transfer on the separation of laminar boundary layers in supersonic flow are considered theoretically and experimentally. In theory, cooling the wall reduces the extent of regions of separation and steepens the pressure gradients, whilst heating the wall has opposite effects. The experimental results partially confirm these predictions. (Author)

Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1960
Accession Number
AD0262626

Entities

People

  • G.e. Gadd

Organizations

  • AGARD

Tags

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Flow
  • Heat Transfer
  • Laminar Boundary Layer
  • Layers
  • Pressure Gradients
  • Supersonic Flow

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers