EFFECT OF A HIGHLY COOLED WALL ON HYPERSONIC TURBULENT HEAT TRANSFER.

Abstract

Turbulent heat-transfer rates were measured on a thin-walled, slender cone in a hypersonic tunnel at a free-stream Mach number of 5.0. Wall-to-stagnation temperature ratios of approximately 0.3 and 0.45 were obtained by cooling the model with liquid CO2. A wide range of test Reynolds numbers were obtained by varying the tunnel supply pressure. This provided data for both laminar and mixed laminar - turbulent boundary-layer conditions. The experimental results are compared with existing theories which predict convective heat-transfer coefficients. These comparisons substantiate the predictions of Winkler and Cha for the present test conditions. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1966
Accession Number
AD0638232

Entities

People

  • Donald M. Wilson
  • Paul D. Fisher

Organizations

  • Naval Ordnance Laboratory

Tags

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Coefficients
  • Fluid Mechanics
  • Free Stream
  • Heat Transfer
  • Heat Transfer Coefficients
  • Layers
  • Mach Number
  • Reynolds Number
  • Stagnation Temperature
  • Turbulent Boundary Layer

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Fluid Mechanics and Fluid Dynamics.
  • Structural Dynamics.

Technology Areas

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