This program is one designed for the calculation of design-point performance of turbojet and turbofan engine cycles. This program requires as input the airplane Mach number, the altitude-state equations, turbine-inlet temperature, afterburner temperature, duct burner temperature, bypass ratio, coolant flow, component efficiences, and component pressure ratios. The output yields specific thrust, specific fuel consumption, engine efficiency, and several component temperatures and pressures. The thermodynamic properties of the gas are expressed as functions of temperature and fuel-to-air ratio. The program is provided with an example case. The program has been implemented on the IBM 7094.

Design point performance of turbojet and turbofan engine cycles

Cycle characteristics and structural configuration of turbojet and turbofan engines for lightweight aircraft

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W. L. Stewart

Papers

Turbojet and turbofan cycle considerations and engine configurations for application in lightweight aircraft