Online Flow Calculator (THRUST/Calc)

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Turbojet engine analysis

Two-spool Turbofan engine analysis

Ramjet engine analysis

Scramjet engine analysis

precision settings

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Turbojet engine analysis

Two-spool Turbofan engine analysis

Ramjet engine analysis

Scramjet engine analysis

Fuel

Design conditions

Design parameters

Fuel

Design conditions

Design parameters

Fuel

Design conditions

Design parameters

Fuel

Design conditions

Design parameters

Fuel

Design conditions

Design parameters

Fuel

Design conditions

Design parameters

Fuel

Design conditions

Design parameters

Fuel

Design conditions

Design parameters

calculator settings

turbojet

Calculation of engine station data for a generic turbojet engine based on provided design parameter values.

Select fuel type

Flight Mach number $\left(M_\infty\right)$
Altitude
Variation to ISA $\left(\Delta \mathrm{ISA}\right)$

Compressor pressure ratio $\left(\Pi_c \right)$
Turbine entry temperature $\left(\mathrm{TET}\right)$
Intake isentropic efficiency $\left(\eta_{in}\right)$
Compressor isentropic efficiency $\left(\eta_{i,c}\right)$
Combustion efficiency $\left(\eta_{b}\right)$
Combustion pressure loss $\left(1-P_4/P_3\right)$
Turbine isentropic efficiency $\left(\eta_{i,t}\right)$
Mechanical efficiency $\left(\eta_{m}\right)$
Nozzle isentropic efficiency $\left(\eta_{n}\right)$
Cooling relative flow $\left(\mathrm{bpr}_c\right)$

turbofan

Calculation of engine station data for a generic two-spool turbofan engine based on provided design parameter values.

Select fuel type

Flight Mach number $\left(M_\infty\right)$
Altitude
Variation to ISA $\left(\Delta \mathrm{ISA}\right)$

Turbine entry temperature $\left(\mathrm{TET}\right)$
Bypass ratio $\left(\mathrm{BPR}\right)$
Intake isentropic efficiency $\left(\eta_{in}\right)$
Fan pressure ratio $\left(\mathrm{FPR} \right)$
Fan isentropic efficiency $\left(\eta_{i,fan}\right)$
LP Compressor pressure ratio $\left(\mathrm{\Pi_{LPC}} \right)$
LP Compressor isentropic efficiency $\left(\eta_{i,LPC}\right)$
HP Compressor pressure ratio $\left(\mathrm{\Pi_{HPC}} \right)$
HP Compressor isentropic efficiency $\left(\eta_{i,HPC}\right)$
Combustion efficiency $\left(\eta_{b}\right)$
Combustion pressure loss $\left(1-P_4/P_3\right)$
HP Turbine isentropic efficiency $\left(\eta_{i,HPT}\right)$
LP Turbine isentropic efficiency $\left(\eta_{i,LPT}\right)$
Mechanical efficiency $\left(\eta_{m}\right)$
Cold nozzle isentropic efficiency $\left(\eta_{n,cold}\right)$
Hot nozzle isentropic efficiency $\left(\eta_{n,hot}\right)$
Cooling relative flow $\left(\mathrm{bpr}_c\right)$

ramjet

Calculation of engine station data for a generic ramjet engine based on provided design parameter values.

Note: calculation output is not yet implemented for the ramjet engine.

Select fuel type

scramjet

Calculation of engine station data for a generic scramjet engine based on provided design parameter values.

Note: calculation output is not yet implemented for the scramjet engine.

Select fuel type

Flight Mach number $\left(M_\infty\right)$
Altitude
Variation to ISA $\left(\Delta \mathrm{ISA}\right)$

Combustor inlet Mach number $\left(M_2\right)$
Combustion efficiency $\left(\eta_{b}\right)$
Nozzle total pressure ratio $\left(\pi_{nozzle}\right)$

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Flight Mach number $\left(M_\infty\right)$

Max flight Mach number $\left(M_\infty\right)$

Variation to ISA $\left(\Delta \mathrm{ISA}\right)$

decimal numbers:
exponential numbers: