Ideal Cycle Gas Turbine Analysis
This web application calculates the thrust and exhaust velocities of an ideal gas turbime using simple thermodynamic theory. As component losses are not part of the prediction, the solver may overpredict performance by 5% to 10%.
Input Parameters
Bypass Ratio :

Fan Pressure Ratio :

Compressor Pressure Ratio :

Fuel/Air Ratio :

Core Exhaust Area (m^2) :

Flight Mach Number :

Altitude (m) :