Can We Calculate Ramjet Thrust Using Combustion Mach Number and Rayleigh Flow?

[tomliu93]

For a ramjet engine, combustion occurs at a finite Mach number M. If we know the ambient conditions like free stream Mach number and pressure and the ratio between the stagnation temperature at the inlet and exit of the combustor, how can we derive the thrust? How can we incorporate the combustion Mach number into calculation? Do we need to consider Rayleigh flow?

 

[Greg Bernhardt]

I'm sorry you are not generating any responses at the moment. Is there any additional information you can share with us? Any new findings?