Low shock strength propulsion system

A supersonic nacelle design employing a bypass flow path internal to the nacelle and around the engine is disclosed herein. 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 sub...

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Bibliographische Detailangaben
1. Verfasser:	CONNERS TIMOTHY R
Format:	Patent
Sprache:	eng
Schlagworte:	AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION BLASTING COMBUSTION ENGINES COMBUSTION ENGINES IN GENERAL COSMONAUTICS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS INTERNAL-COMBUSTION PISTON ENGINES JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING PARACHUTES PERFORMING OPERATIONS TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	A supersonic nacelle design employing a bypass flow path internal to the nacelle and around the engine is disclosed herein. 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.