MEASUREMENT OF HEAT TRANSFER AT NOZZLE THROAT BY IMBEDDED PYROMETER METHOD,

Abstract

A newly developed transistorized radiation pyrometer was employed in temperature and heat transfer studies of the nozzle of a rocket exhaust powered Mach 5 hypersonic wind tunnel. The investigation also involved boundary layer measurements and spectroscopic determination of gas species concentration.

Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1964
Accession Number
AD0631821

Entities

People

  • F. K. Hill
  • S. A. Elder

Organizations

  • Johns Hopkins University Applied Physics Laboratory

Tags

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Gases
  • Heat Transfer
  • Hypersonic Wind Tunnels
  • Layers
  • Measurement
  • Measuring Instruments
  • Pyrometers
  • Radiation
  • Radiation Pyrometers
  • Rocket Exhaust
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Combustion science or combustion engineering.
  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flight
  • Hypersonics - Hypersonic Flow