Low shock strength propulsion system

A low shock supersonic nacelle, comprising:

• an engine;
• an outer wall;
• a bypass wall disposed within the outer wall and configured to support the engine;
• a set of struts configured to couple the outer wall with the bypass wall, a first sub-set of the set of struts having a first curvature that directs the bypass flow portion in a first circumferential direction around a protruding portion of the supersonic engine, a second sub-set of the set of struts having a second curvature that directs the bypass flow portion in a second circumferential direction around a protruding portion of the supersonic engine, a third sub-set of the set of struts disposed downstream of the first sub-set and having a third curvature that directs the bypass flow portion in the second circumferential direction, and a fourth sub-set of the set of struts disposed downstream of the second sub-set and having a fourth curvature that directs the bypass flow portion in the first circumferential direction;
• an inlet defined by front portions of the outer wall and the bypass wall, the inlet configured to decelerate an incoming airflow to a speed compatible with the engine;
• and
• a nozzle defined by rear portions of the outer wall and the bypass wall, the nozzle configured to accelerate an exhaust from the engine and bypass, wherein the bypass wall divides the incoming airflow into a primary flow portion directed into the engine and a bypass flow portion directed into a bypass that bypasses the engine, the bypass flow portion comprising a subsonic flow,
• wherein the inlet comprises an external compression inlet having an external compression surface upstream of the engine and the bypass, and
• wherein the set of struts is further configured to direct the bypass flow portion around the engine and to expand the bypass flow portion into a supersonic exhaust.

A nacelle for a supersonic engine, comprising:

• an outer wall defining a closed volume;
• a bypass wall disposed within the closed volume of the outer wall, the outer wall and the bypass wall cooperating to form a bypass that bypasses the supersonic engine;
• a set of vanes configured to couple the outer wall with the bypass wall, defining a bypass therebetween, the set of vanes directing a bypass airflow into a subsonic flow, the set of vanes further configured to direct the subsonic flow around the supersonic engine and to expand the subsonic flow into a supersonic exhaust, a first sub-set of the set of vanes having a first curvature that directs the bypass flow portion in a first circumferential direction around a protruding portion of the supersonic engine, a second sub-set of the set of vanes having a second curvature that directs the bypass flow portion in a second circumferential direction around a protruding portion of the supersonic engine, a third sub-set of the set of vanes disposed downstream of the first sub-set and having a third curvature that directs the bypass flow portion in the second circumferential direction, and a fourth sub-set of the set of vanes disposed downstream of the second sub-set and having a fourth curvature that directs the bypass flow portion in the first circumferential direction;
• and
• an external compression inlet having an external compression surface upstream of the supersonic engine and the bypass.

A low shock supersonic nacelle, comprising:

• an engine;
• an outer wall defining a closed volume;
• a bypass wall disposed within the closed volume of the outer wall and configured to support the engine;
• a set of vanes configured to couple the outer wall with the bypass wall, a first sub-set of the set of vanes having a first curvature that directs the bypass flow portion in a first circumferential direction around a protruding portion of the supersonic engine, a second sub-set of the set of vanes having a second curvature that directs the bypass flow portion in a second circumferential direction around a protruding portion of the supersonic engine, a third sub-set of the set of vanes disposed downstream of the first sub-set and having a third curvature that directs the bypass flow portion in the second circumferential direction, and a fourth sub-set of the set of vanes disposed downstream of the second sub-set and having a fourth curvature that directs the bypass flow portion in the first circumferential direction;
• an inlet defined by front portions of the outer wall and the bypass wall, the inlet configured to decelerate an incoming airflow to a speed compatible with the engine, the bypass wall dividing the incoming airflow into a primary flow portion directed into the engine and a bypass flow portion directed into a bypass that bypasses the engine, the bypass flow portion comprising a subsonic flow;
• and
• a nozzle defined by rear portions of the outer wall and the bypass wall, the nozzle configured to accelerate an exhaust from the engine and the bypass,
• wherein the inlet comprises an external compression inlet having an external compression surface upstream of the engine and the bypass,
• wherein the set of vanes is further configured to direct the bypass flow portion around the engine and to expand the bypass flow portion into a supersonic exhaust.