| 摘要 |
Examples of the invention relate to a supersonic nacelle design employing a bypass flow path internal to the nacelle and around the engine. A set of aerodynamic vanes may be used to shape a supersonic airflow within a bypass around an engine. The vanes may be capable of compressing the supersonic airflow into a subsonic airflow, direct the subsonic airflow around the engine, and then expand the subsonic airflow into a supersonic exhaust. The vanes may shape the airflow by reducing sonic boom strength, cowl drag, and airframe interference drag.
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