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Performance Jet Engines Excel Spreadsheet

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Ideal and non-ideal performance of turbojet, turbofan and ramjet engines excel spreadsheet calculator.

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Download: Ideal and non-ideal performance of turbojet, turbofan and ramjet engines excel spreadsheet calculator.

Default flight Mach number
Default specific heat ratio (same throughout cycle unless overridden)
Default gas molecular weight (kg/mole) (assumed constant throughout cycle)
Default ambient temperature (K)
Default ambient pressure (atm)
Default inlet diffuser efficiency
Specific heat ratio for diffuser (default value = gamma_default)
Default compressor pressure ratio
Default compressor efficiency
Specific heat ratio for compressor (default value = gamma_default)
Default fan pressure ratio
Default fan efficiency
Specific heat ratio for fan (default value = gamma_default)
Default bypass ratio (mass flow through fan / mass flow through core stream)
Default afterburner on/off (false = no afterburner)
Default value of (turbine inlet temperature limit /ambient temperature)
Default burner pressure ratio
Default burner efficiency (actual fuel input / ideal fuel input if no heat losses)
Specific heat ratio for burner (default value = gamma_default)
Default turbine efficiency
Specific heat ratio for turbine (default value = gamma_default)
Default value of (afterburner temperature limit /ambient temperature)
Default afterburner pressure ratio
Default afterburner efficiency (actual fuel input / ideal fuel input if no heat losses)
Specific heat ratio for afterburner (default value = gamma_default)
Exit pressure (atm) (default = ambient pressure)
Default nozzle efficiency
Specific heat ratio for nozzle (default value = gamma_default)
Inlet drag coefficient (drag/area = drag_coeff*(1/2)*rho*u1^2)
Fuel heating value (J/kg)

Credit:
Paul Ronney
University of Southern California


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