OPTIMIZATION OF A SCRAMJET CONFIGURATION.
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
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The configuration optimization study was conducted to analytically determine the two dimensional cruise configuration of a Mach ten hydrogen-fueled scramjet vehicle that provided maximum cruise range. Two combustion processes, constant area and constant pressure, and three configuration variables inlet compression angle, nozzle expansion angle, and the angle of the top surface of the vehicle relative to the direction of flight were considered. A computerized open loop search for the optimum configuration was conducted. Within the constraints of the problem, the vehicle with constant area combustion had a better cruise range than the vehicle with constant pressure combustion. Author
- Fluid Mechanics
- Combustion and Ignition
- Jet and Gas Turbine Engines