TEMPERATURE-TIME HISTORY OF RIGHT CIRCULAR CYLINDER IN HYPERSONIC FLOW,

Abstract

A solution of the problem of unsteady heat transfer to a right circular cylinder in laminar hypersonic flow was found. The solution is based upon the assumption that the heat transfer to the surface of the cylinder is proportional to the cosine of the angle measured from the stagnation point. The solution is expected to be valid within 70 degrees of the stagnation point. (Author)

Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1968
Accession Number
AD0680004

Entities

People

  • James S. Petty
  • Ronald A. Briggs

Organizations

  • Air Force Research Laboratory

Tags

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Energy Transfer
  • Flow
  • Fluid Dynamics
  • Fluid Flow
  • Heat Transfer
  • Hypersonic Flow
  • Stagnation Point

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.

Technology Areas

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