Supersonic ramjet behind the aft of the flying vehicle

The scheme of a supersonic ramjet, the combustion chamber of which is located behind the end wall of the aft of the flying vehicle, is considered. A numerical experiment is being carried out to simulate the combustion of hydrogen at an altitude of 16 km with a flight Mach number equal to 9. It is shown that the proposed engine scheme implements diffusion combustion, which under similar flight conditions is several times higher than continuous detonation combustion of hydrogen in a nozzle direct-flow combustion chamber in terms of the efficiency, specific thrust and impulse.