A Summary of the Factors Influencing the Extent of Separation of a Laminar Boundary Layer Due to a Compression Corner at Moderately Hypersonic Speeds.

Abstract

A summary is presented of the effects of flow and geometric factors on the extent of separation of a laminar boundary layer. Consideration is given to the Mach number, Reynolds number, wall to free stream temperature ratio, hinge line mass transfer, span and chord dimensions of the model and compression surface, and the angle of deflection of the compression surface. The results are presented as analytical and correlated expressions to determine the basic parameters of the separation phenomenon for engineering design estimates. (Author)

Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1971
Accession Number
AD0729446

Entities

People

  • Karlheinz O. W. Ball

Organizations

  • Ohio State University

Tags

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Compression
  • Deflection
  • Engineering
  • Flow
  • Fluid Mechanics
  • Free Stream
  • Laminar Boundary Layer
  • Layers
  • Mach Number
  • Mass Transfer
  • Reynolds Number

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Structural Dynamics.
  • Theoretical Analysis.

Technology Areas

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