THE COMPRESSIBLE BOUNDARY LAYER,

Abstract

The laminar boundary layer equations in integral form are solved on the mechanical differential analyzer. The method of analysis permits the use of the best known variation of the air properties with temperature. Solutions are obtained for Mach numbers ranging from incompressible speeds to the hypersonic regime at ambient temperatures of 100, 400 and 800R for both insulated plate and heat transfer cases. From these results an approximate design procedure for the calculation of the characteristics of both the laminar and turbulent boundary layers is obtained and presented as an aid to missile designers. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1951
Accession Number
AD0623563

Entities

People

  • Earl Janssen
  • George B. W. Young

Organizations

  • RAND Corporation

Tags

DTIC Thesaurus Topics

  • Analyzers
  • Boundaries
  • Boundary Layer
  • Differential Analyzers
  • Equations
  • Heat Transfer
  • Laminar Boundary Layer
  • Layers
  • Mach Number
  • Turbulent Boundary Layer

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.
  • Structural Dynamics.
  • Thermal Physics or Thermal Science.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Microelectronics
  • Microelectronics - Graphene
  • Microelectronics - Microelectromechanical Systems