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Flowfield Characterization in a LOX/GH2 Propellant RocketThe 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.
Document ID
19950017222
Acquisition Source
Headquarters
Document Type
Conference Paper
Authors
Pal, S. (Pennsylvania State Univ. University Park, PA, United States)
Moser, M. D. (Pennsylvania State Univ. University Park, PA, United States)
Ryan, H. M. (Pennsylvania State Univ. University Park, PA, United States)
Foust, M. J. (Pennsylvania State Univ. University Park, PA, United States)
Santoro, R. J. (Pennsylvania State Univ. University Park, PA, United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1993
Publication Information
Publication: NASA. Marshall Space Flight Center, Eleventh Workshop for Computational Fluid Dynamic Applications in Rocket Propulsion, Part 1
Subject Category
Fluid Mechanics And Heat Transfer
Accession Number
95N23642
Funding Number(s)
CONTRACT_GRANT: NAS8-38862
CONTRACT_GRANT: NAGW-1356
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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