LAMINAR SEPARATION IN SUPERSONIC FLOW.

Abstract

Detailed experimental investigations were made at a Mach number of 2.21 of laminar flows over ramps, backward facing steps and swept back wings. Large spanwise variations of the heat transfer coefficient (h) were measured, with two different techniques, in the reattachment region of the flow over a backward facing step and were related to streamwise vortices present in the laminar boundary layer. Peaks in h much larger than the turbulent value were measured. By comparing spanwise total head and heat transfer rate distributions, Reynolds analogy was found to apply quantitatively for reattaching flows with streamwise vortices. The effect of free-stream Reynolds number and of leading edge sweep, accuracy of machining, thickness and bevel angle on the intensity of streamwise vortices present in the boundary layer on swept back wings was investigated. Flow separation was detected at the leading edge. A regular pattern of streamwise vortices of small wave length was observed outside of the boundary layer.

Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1964
Accession Number
AD0612407

Entities

People

  • Jean J. Ginoux

Tags

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Flow
  • Flow Separation
  • Free Stream
  • Heat Transfer
  • Heat Transfer Coefficients
  • Laminar Boundary Layer
  • Laminar Flow
  • Layers
  • Leading Edges
  • Mach Number
  • Reynolds Number
  • Supersonic Flow
  • Sweptback Wings

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers