A parametric investigation was made of a series of lowmolecular-weight, high-hydrogen-content compounds as propellants for nuclear-powered rockets. The chemical compounds include H/sub 2/, NH/sub 3/, H/sub 2/0, LiH, CH/sub 4/, and CH/ sub 3/OH. A two-part computational program was carried out for each compound; the results for methane are presented in both tabular and graphic form. The results of the first part of the program are presented in static form, that is, by the conventional Mollier diagram, in which specific enthalpy is plotted against specific entropy, with cross plots of temperature, pressure, and molecular weight. The results of the second part of the program are presented in dynamic form by a series of diagrams in which specific impulse is plotted against pressure, with cross plots of chamber temperature, exhaust temperature, and rocket-nozzle area. It was assumed that the propellant gas, starting with a nonzero chamber velocity, maintained instantaneous chemical equilibrium composition as it expanded isentropically through a de LavaI nozzle. (auth)