HYPERVELOCITY STAGNATION POINT HEAT TRANSFER

Abstract

The results of a new theoretical analysis of the effects of ionization on hypervelocity stagnation point heat transfer, and experimental data obtained in a newly developed hypervelocity shock tube are presented for flight conditions ranging from orbital to superorbital velocities,AND COMPARED WITH EXISTING THEORIES. On the basis of the new theoretical results and the experimental data, it appears that the convective heat transfer rate encountered by a re-entry space vehicle entering the earth's atmosphere at escape velocity is more than twice as large as predicted by existing theories. (Author)

Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1961
Accession Number
AD0270935

Entities

People

  • Sinclaire M. Scala
  • Walter R. Warren

Organizations

  • General Electric

Tags

DTIC Thesaurus Topics

  • Atmospheres
  • Escape Velocity
  • Experimental Data
  • Heat Transfer
  • Ionization
  • Shock Tubes
  • Spacecraft
  • Stagnation Point
  • Tubes
  • Vehicles

Fields of Study

  • Physics

Readers

  • Combustion science or combustion engineering.
  • Fluid Dynamics.
  • Missile Defense Systems.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flight
  • Hypersonics - Hypersonic Flow
  • Space
  • Space - Hall-Effect Thruster
  • Space - Orbital Debris