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This diagram deals with SR-71 thrust division.
The actual engine (2-3) only provides about 17% of the propulsive thrust at high Mach numbers. The remainder results from the integrated pressure distribution at the walls of the inlet system and the ejector nozzle. The contribution of the inlet system consists of 14% drag, which acts on the front part of the cone (0-1) and 70% thrust, which is generated in the subsonic diffuser (1-2). The component of the ejector nozzle (3-4) amounts to 27% thrust.
At maximum Mach numbers, the task of the engine is to maintain the flow necessary to generate thrust inside the propulsion system, while its contribution to the thrust balance is minimal. At low speeds, on the other hand, the largest part of the thrust is generated in the engine.
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