Liquid hydrogen has been classed as a high energy fuel for rocket propulsion. A survey of the latest technical literature was made and the information compiled in a form which discusses the value of this fuel in propellant combinations. Thermodynamic performance, payload comparisons, advantages, disadvantages, problems, and relative merits of respective combinations and systems are presented. A discussion of rocket performance parameters is included as a basis for a more complete understanding of the information presented in the above-mentioned areas. (Author)


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