Design and Stream Thrust Analysis of a Scramjet Engine for Acceleration Mission from 2 to 3 km/s

Stream thrust analysis was used for preliminary performance evaluation of a hydrogen powered scramjet engine on an acceleration mission from 2 to 3 km/s at 30 km altitude. An inward two-dimensional scramjet inlet was chosen along with an axial injection combined with step combustor. The expansion was modeled with quasi-one-dimensional flow equations. All of the engine geometry was considered variable as a function of the trajectory. Three acceleration strategies were defined, one with a constant stoichiometric fuel-air mixture , and other two with the parameter set as 0.2 and 0.5. All of them produced high specific thrust and high specific impulse throughout the acceleration. For the first case, the specific thrust decreased with flight velocity while the contrary was observed for the latter two cases. The specific impulse decreased and no significant difference was found in the cases studied. The overall efficiency followed this same behavior. The required engine geometry change was clearly more accentuated for the case of

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