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EFFECT 0F SELECTED DESIGN MODIFICATI0NS 0N ENGINE CHARACTERISTICS
LIST 0F SYMB0LS
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approximately assumed axial beryllium oxide beta particles Btu/sec CAVITY PROPELLANT ENTHALPY cavity propellant flow configuration Contract NASw-847 coolant fluid COOLANT HOLE DIAMETER coolant passage COOLANT VOLUME FRACTION cooling holes CRITICAL FUEL DENSITY critical mass curved ducts cylindrical dynamic pressure EMPLOYED IN REF ENGINE WEIGHT fuel-containment region Gaseous Nuclear Rocket given in Fig heat deposition Heat Transfer heavy water heavy-water helium high-temperature heat exchangers hydrogen inlet laminar flow instability lb/sec liner tubes Low-Temperature Heat Exchanger maraging steel NASA niobium carbide nozzle nozzle entrance nuclear rocket engine percent prepared by UAC prepared under Contract Pressure Loss pressure vessel propellant injection PYROLYTIC GRAPHITE report classified Confidential report unclassified Research Laboratories Report Reynolds number shown in Fig specific impulse STANDARD VALUES studies of Ref Systems Command Report Table XV tungsten turbine turbopump UAC Research Laboratories velocity Vortex Tube Vortex-Stabilized Gaseous Nuclear