Accession Number:

AD0239465

Title:

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

Descriptive Note:

Corporate Author:

ARO INC ARNOLD AFS TN

Personal Author(s):

Report Date:

1960-06-01

Pagination or Media Count:

46.0

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.

Subject Categories:

  • Liquid Propellant Rocket Engines
  • Combustion and Ignition

Distribution Statement:

APPROVED FOR PUBLIC RELEASE