Some Studies of the Flow Pattern at the Base of Missiles with Rocket Exhaust Jets

Abstract

The problem of the recirculation of hot exhaust gases into the engine compartment at the base of a missile has been investigated. Cold flow nozzles were used to simulate the rockets at the base of a missile model, and various tracer techniques were used to visually show the flow pattern at the base. Results are presented for a two-nozzle exploratory model and for various base configurations of the Atlas missile. Similarity parameters for simulating jet exhausts and their application to these investigations are discussed.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1960
Accession Number
AD0239465

Entities

People

  • B. H. Goethert
  • L. T. Barnes

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Ballistic Missiles
  • Base Flow
  • Boundaries
  • Combustion
  • Creep
  • Engines
  • Exhaust Gases
  • Flow
  • Fuel Systems
  • Gases
  • Mach Number
  • Models
  • Rocket Engines
  • Rocket Exhaust
  • Rocket Models
  • Rockets
  • Test Facilities

Readers

  • Combustion and Flow Dynamics.
  • Rocket Propulsion.