Studies of turbojet engines for hypersonic propulsion.

This thesis contains the results of a theoretical analysis of the performance of an inverted turbojet cycle as a thrust power unit. This system is compared with a conventional turbojet with and without reheat and pre-cooling. Within the limitations of the analysis it is seen that the domain of air breathing engines for propulsion can be extended to hypersonic vehicles. The inverted turbojet is an economical cruising engine for hypersonic vehicles at Mach numbers 5-6. However a conventional turbojet with pre-cooling and reheat can power a vehicle throughout the range of Mach 0 to Mach 6