LEADING EDGE EFFECT ON SEPARATED SUPERSONIC FLOWS

Abstract

IN SUPERSONIC TUNNEL TESTS WITH A TWO-DIMENSIONAL BACKWARD-FACING STEP MODEL, SPAN-WISE PERTURBATIONS WERE FOUND IN THE REATTACHMENT REGION. Studies were made using the same and other similar models. In these later studies, the same three-dimensional perturbations were detected, into the full thickness of the boundary-layer, after reattachment, both in turbulent and laminar regions of the flow. Their amplitude was a maximum in the transition region. Using a model with a much improved accuracy of manufacture, notably at the leading-edge, it was found that the amplitude of the perturbations was greatly reduced, roughly in proportion to the size of the irregularities of manufacture of the leadingedge itself. It is concluded that the phenomenon is essentially one of instability in the twodimensional flow, the main triggering action arising from small irregularities in the leadingedge. (Author)

Document Details

Document Type
Technical Report
Publication Date
May 01, 1961
Accession Number
AD0262031

Entities

People

  • Jean J. Ginoux

Tags

DTIC Thesaurus Topics

  • Accuracy
  • Amplitude
  • Boundaries
  • Boundary Layer
  • Flow
  • Geometry
  • Instability
  • Layers
  • Leading Edges
  • Mathematics
  • Perturbations
  • Physical Properties
  • Sizes (Dimensions)
  • Supersonic Flow
  • Three Dimensional
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.
  • Systems Analysis and Design

Technology Areas

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