I have to derive an equation that determines the stagnation temperature at the turbine inlet for a turbofan engine, from some data that was measured during an experiment. The data I have: engine RPM Exhaust stagnation temperature fuel consumption thrust To=16C Po=101kPa I have done through a fair few derivations, but keep coming up with an equation that has a mass flow rate term. Of course, this isn't included in my data. Is there a way to work out the mass flow rate using only the information I have been given? Do I even need the mass flow rate, or is there a simpler way to work things out? Cheers.