EQUILIBRIUM TOTAL RADIATION MEASUREMENTS IN AIR AT SUPERORBITAL ENTRY VELOCITIES,

Abstract

An experimental investigation was carried out to obtain data on the total radiance of air at elevated temperatures. The experiment was performed in a 3-in. I.D. combustion-driven shock tube. The heat-transfer model used in this investigation was a flat-nosed cylinder approximately 1.13 in. in diameter. The radiation from the gas in the shock layer was measured by a thinfilm gage placed behind a quartz window. The gage was placed about 0.5 in. behind the quartz window so that the radiating gas which the gage sees is a truncated cone with height equal to the shock-detachment distance. The data obtained are in good agreement with both the theoretical predictions by Nardone, Breene, Zeldin, and Riethof of General Electric and those by Meyerott, Sokoloff, and Nicholls of Lockheed Missiles and Space Company. (Author)

Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1963
Accession Number
AD0424935

Entities

People

  • H. Hoshizaki

Organizations

  • Lockheed Martin Missiles and Space

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Agreements
  • Burning Rate
  • Chemical Reaction Properties
  • Chemical Reactions
  • Combustion
  • Diameters
  • Energy Transfer
  • Heat Transfer
  • Measurement
  • Physical Properties
  • Radiance
  • Radiation
  • Shock Tubes
  • Tubes

Fields of Study

  • Physics

Readers

  • Combustion science or combustion engineering.
  • Fluid Dynamics.
  • Spectroscopy.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster