This work is focused on performance analysis of a turbojet engine with an inlet flow control mechanism for
same thrust values. Developed a real-time turbojet engine integrating aerothermodynamics of engine components, principles
of jet propulsion and inter component volume dynamics represented in 1-D non-linear unsteady equations. Performance
parameters of the engine are analyzed with the increase in compressor pressure ratio. Specific fuel consumption, specific
thrust, component pressure ratios, thermal and propulsive efficiencies are the performance parameters of the engine that are
analyzed on the model with reduced inlet pressure. All simulations will be done on MATLAB Tool.
