Computation of the Skin-Friction and Heat Transfer on a Sharp Cone in Axisymmetric Turbulent Hypersonic Flow,

Abstract

A computer program has been written to determine the skin-friction coefficient and heat-transfer rate on a sharp cone in axisymmetric hypersonic flow with a turbulent boundary layer. The methods of Spalding and Chi, Sommer and Short, and Van Driest transformations between the incompressible and compressible planes. The Karman-Schoenherr flat plate equation is used to relate the incompressible skin friction to Reynolds number based on momentum thickness. A listing of the program is also included in the report. (Author)

Document Details

Document Type
Technical Report
Publication Date
Apr 12, 1973
Accession Number
AD0761602

Entities

People

  • Stephen Sacks

Organizations

  • Naval Ordnance Laboratory

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Axisymmetric
  • Boundary Layer
  • Coefficients
  • Computer Programs
  • Computers
  • Flow
  • Friction
  • Heat Transfer
  • Hypersonic Flow
  • Layers
  • Reynolds Number
  • Skin Friction
  • Turbulent Boundary Layer

Fields of Study

  • Physics

Readers

  • Computer Science.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers