EFFECT OF MACH NUMBER ON STREAMWISE VORTICES IN LAMINAR REATTACHING FLOWS.

Abstract

An experimental investigation was made in various supersonic and hypersonic wind tunnels to determine the effect of Mach number on the existence of streamwise vortices in the reattachment region of the flow over twodimensional backward facing steps. It was found that the phenomenon previously observed at M = 2.21 remained unchanged over a Mach number range of 1.5 to 7.0. The ratio of the wave length of the vortices to the boundary layer thickness at separation varied slightly with free stream Mach number, with a maximum at about M = 3. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1965
Accession Number
AD0623460

Entities

People

  • Jean J. Ginoux

Organizations

  • von Kármán Institute for Fluid Dynamics

Tags

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Flow
  • Free Stream
  • Hypersonic Wind Tunnels
  • Layers
  • Mach Number
  • Thickness
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.
  • Mathematics or Statistics

Technology Areas

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