Method for streamline traced external compression inlet

A method for diverting boundary layer air from a ducted inlet comprising:

• altering the path of the boundary layer air flowing toward the ducted inlet by placing a compression surface on a body to which the ducted inlet is coupled in the path of the boundary layer air;
• and
• creating a pressure differential in the interior of the ducted inlet by coupling a cowl to the body, wherein the cowl is operable to substantially prevent the boundary layer air from entering the ducted inlet;
• wherein:
• the compression surface is defined by streamline traces of free stream air from seed points;
• the opening of the ducted inlet is defined by streamline traces of free stream air from seed points;
• an upstream-most shock comprises an oblique shock derived from the forward-most section of a flow field generator within a supersonic flow field;
• and
• a downstream-most shock comprises a oblique shock derived from the aft-most section of a flow field generator within the supersonic flow field, wherein a surface duplicated from the downstream-most shock system is translated downstream to allow spillage of air from the ducted inlet.

A method operable to determine external compression surfaces associated with a ducted inlet comprising:

• producing one or more oblique shocks based on compression requirements associated with the ducted inlet;
• modeling oblique shock shapes associated with the produced shock system;
• projecting an aperture segment corresponding to a leading edge of the inlet compression surface onto a modeled forward-most oblique shock, wherein an intersection of a first shock and aperture segment define a leading edge of the external compression surface;
• producing streamline traces from the leading edge of the external compression surface, wherein the streamline traces define the external compression surface;
• and
• projecting a cowl shape onto a duplicated aft-most oblique shock, wherein an intersection of the duplicated aft-most shock and the cowl shape define a leading edge of the cowl.

A method operable to determine external compression surfaces associated with a ducted inlet coupled to an engine face, the method comprising:

• defining the compression requirements for the ducted inlet;
• producing one or more oblique shocks based on the compression requirements;
• modeling oblique shock shapes associated with one or more oblique shocks;
• translating a surface duplicated from a aft-most oblique shock downstream to induce spillage of airflow over the ducted inlet;
• projecting an aperture segment onto a forward-most oblique shock, wherein an intersection of a upstream oblique shock and the aperture segment define a leading edge of the external compression surface, and wherein the streamlines originate from seed points within the leading edge of the external compression surface;
• producing streamline traces from the leading edge of the external compression surface, wherein the streamline traces define the external compression surface;
• projecting a cowl shape onto a surface duplicated from the aft-most oblique shock, wherein an intersection of the surface and the cowl shape define a leading edge of the cowl.
• producing streamline traces from the leading edge of the cowl, wherein the streamline traces define an external surface of the cowl, and wherein the streamlines originate from seed points within the leading edge of the cowl;
• and
• lofting the compression surface to an internal surface of the ducted inlet.