ROCKET EXPERIMENTS ON THE HEAT TRANSFER TO A PROTUBERANCE AND TO A CAVITY.

Abstract

Temperature measurements on a protuberance and a cavity mounted on a Black Brant III sounding rocket are reported. These are analysed to give distributions of local heat transfer coefficients. Supporting wind tunnel measurements of surface pressures and surface flow visualization are also presented. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1968
Accession Number
AD0682525

Entities

People

  • R. F. Meyer

Organizations

  • National Research Council Canada

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Coefficients
  • Flow
  • Flow Visualization
  • Heat Transfer
  • Heat Transfer Coefficients
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Rockets
  • Sounding Rockets
  • Wind Tunnels

Readers

  • Fluid Mechanics and Fluid Dynamics.
  • Space/Atmospheric Physics.