SHOCK GENERATORS IN THE HYPERSONIC TURBULENT BOUNDARY LAYER.

Abstract

In order to reduce the heat transfer and skin friction in a turbulent supersonic boundary layer, a totally immersed shock generator is employed. Values of wall heat transfer, skin friction, shock generator heat transfer and drag, and profiles of flow quantities downstream are obtained experimentally for several configurations. The boundary layer returns to a similar but thicker boundary layer within 20 boundary layer thicknesses downstream of the shock generator. Heat transfer and skin friction reductions of 8% to 27% are obtained. (Author)

Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1967
Accession Number
AD0661992

Entities

People

  • Richard Gorman

Organizations

  • New York University

Tags

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Drag
  • Friction
  • Generators
  • Heat Transfer
  • Layers
  • Skin Friction
  • Turbulent Boundary Layer

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.

Technology Areas

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