  This paper discusses the analysis performed on a supersonic ramjet engine
inlet for flight in the atmosphere of Jupiter. Since the Jovian atmosphere
lacks oxygen, the thrust will be generated by nuclear fission heating in the
heat chamber. The first task to solve in the design in a ramjet engine is to
design the supersonic inlet. The developed design methodology utilizes
theoretical calculations and Computational Fluid Dynamics (CFD) simulations.
The analytical model used to calculate the gas parameters in front of the heat
chamber, and the CFD analysis, used to define the inlet geometry, are
discussed. The results from the analytical model and CFD are compared and used
for validation of the design approach. The calculated pressure losses and the
mass flow allow the determination of important parameters required for the
design of the aircraft, such as the reactor power, the thrust, the maximum
mass, and the overall external dimensions.
