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

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Calculating ramjet thrust involves understanding the combustion Mach number and its relationship with ambient conditions such as free stream Mach number and pressure. The thrust can be derived by analyzing the stagnation temperature ratio between the inlet and combustor exit. Incorporating the combustion Mach number is essential for accurate thrust calculations, and Rayleigh flow considerations may also play a role in the analysis. The discussion seeks additional insights or recent findings to enhance the understanding of these calculations. Overall, a comprehensive approach is necessary to effectively calculate ramjet thrust.
tomliu93
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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?
 
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