NASA NTRS · 19950017222
Flowfield Characterization in a LOX/GH2 Propellant Rocket
Abstract
The objective of the current work is to experimentally characterize the flowfield associated with an uni-element shear coaxial injector burning liquid oxygen/gaseous hydrogen (LOX/GH2) propellants. These experiments were carried out in an optically-accessible rocket chamber operating at a high pressure (approximately 400 psia). Quantitative measurements of drop size and velocity were obtained along with qualitative measurements of the disintegrating jet.
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Pal, S., Moser, M. D., Ryan, H. M., Foust, M. J., Santoro, R. J.. 1993-07-01. Flowfield Characterization in a LOX/GH2 Propellant Rocket. https://ntrs.nasa.gov/citations/19950017222
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