An exposition of the need of supersonic aircraft to have a variable geometry intake and a fully variable convergent‐divergent nozzle for optimum performance. POWERPLANTS for supersonic aircraft bear only a superficial resemblance to the propulsive units of their subsonic counterparts. A typical subsonic turbojet powerplant consists of a high compression engine with a short fixed intake, and, possibly, a variable convergent nozzle. The supersonic aircraft on the other hand requires a powerplant with a sophisticated variable geometry intake having its own automatic control system and a fully variable convergent‐divergent nozzle in order to extract the full performance throughout the speed range from the slightly lower pressure ratio engine.
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