This work addresses the performance characteristics of hypersonic single-stage-to-orbit (SSTO) vehicles, and develops simple, graphics-based analysis methods appropriate for this class of vehicle. We seek to determine how critical aerodynamic and propulsive characteristics affect the performance of a generic hypersonic vehicle, with regards to a single-stage-to-orbit (SSTO) mission. Toward this end, the energy-state approximation is applied to evaluate these performance measures for the SCRAMjet powered phase of the mission. Fuel-optimization results previously obtained for this vehicle are further analyzed, so that the critical aspects that drive the vehicle's behavior can be identified, as well as the effects of changes in these features. The specific issues considered include sizing, combustion efficiency, parasite drag, engine diffuser and nozzle characteristics, and lift-to-drag.
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