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

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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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