Abstract
An idealized pulse detonation engine (PDE) based on a realistic system concept is defined for which propulsive performance is significantly greater than that of a ramjet over a large range of Mach numbers. An analytical model of the system is developed that calculates physical, timing and flow parameters that can be used as input to multi -dimensional computational fluid dynamics (CFD) analyses and provide a starting point for real system design. A parametric study of the influence on propulsive performance of flight Mach number, inlet pressure recovery, l ength of the detonation tube, mass flow rate of air through the engine, percentage purge and the tube filling strategy is performed with an analytical model and a one -dimensional code based on the method of characteristics. Finally, in a sample engine des ign exercise a PDE based system is specified for which propulsive performance for steady flight is significantly greater than that of a ramjet .
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