Validation of high aspect ratio cooling in a 89 kN (20,000 lb[sub f]) thrust combustion chamber View on Open Library

Validation of high aspect ratio cooling in a 89 kN (20,000 lb[sub f]) thrust combustion chamber

by Mary F. Wadel

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First published: 1996 1 language
Subjects
High aspect ratio Rocket engines Performance tests Mass flow Cooling Thrust chambers Combustion chambers Liquid hydrogen

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