AN ESTIMATE OF COMPRESSIBLE BOUNDARY LAYER DEVELOPMENT AROUND A CONVEX CORNER IN SUPERSONIC FLOW.

Abstract

An analysis of the effect of a sharp convex corner on the momentum thickness of a compressible, supersonic boundary layer flow is presented. The problem is attacked by a momentum integral technique in which an approximate pressure field is used. The shape factor is approximated by a simple expression which is also of general application. The main result of the analysis is an analytic expression for the ratio of the momentum thicknesses downstream and upstream of the corner. The results are also presented graphically over appropriate ranges of the major flow parameters. (Author)

Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1964
Accession Number
AD0609975

Entities

People

  • B. L. Hunt
  • M. Sibulkin

Organizations

  • Brown University

Tags

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Boundary Layer Flow
  • Flow
  • Fluid Flow
  • Integrals
  • Layers
  • Mathematics
  • Momentum
  • Supersonic Flow
  • Thickness

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers