Heat Transfer Rates to 1/50th Scale Models of the Atlas Forebody with G. E. Mark II and AVCO Series 4 Reentry Body Configurations

Abstract

Heat transfer measurements were made in a high temperature wind tunnel on 1/50th scale models of the Atlas forebody with the Mark II and other reentry bodies. The tests were made to provide data to be utilized in heat transfer calculations on the Atlas missile forebody.

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Document Details

Document Type
Technical Report
Publication Date
Apr 04, 1961
Accession Number
AD0843523

Entities

People

  • R. A. Maraschin

Organizations

  • General Dynamics

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Aircraft Engines
  • Blunt Bodies
  • Boundaries
  • Boundary Layer
  • Engineering
  • Exhaust Gases
  • Flow
  • Heat Transfer
  • Heat Transmission
  • High Temperature
  • Hypersonic Wind Tunnels
  • Models
  • Scale Models
  • Static Pressure
  • Turbulent Boundary Layer
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Combustion and Flow Dynamics.
  • Software Engineering