Blended wing aircraft

A blended wing aircraft defining a longitudinal direction and a lateral direction, the blended wing aircraft comprising:

• a body;
• a pair of wings extending outward from the body along the lateral direction;
• and
• a propulsion system comprising an engine mounted to the body, the engine defining an axial direction and having a combustion section and a fan, the fan positioned downstream of the combustion section along the axial direction;
• wherein the body defines a trailing edge and a flowpath surface, wherein the engine is mounted at the trailing edge, and wherein the flowpath surface defines an inlet channel for the engine;
• wherein the engine is a gas turbine engine comprising a turbomachine, wherein the fan is driven by the turbomachine, wherein the turbomachine defines a turbomachine inlet, and wherein the inlet channel extends to the turbomachine inlet;
• wherein the flowpath surface further defines a deflection bump located upstream of the inlet channel or positioned within the inlet channel;
• wherein the deflection bump defines an apex and a bump height (HB) at the apex, wherein turbomachine inlet defines an inlet diameter (DI), and wherein the bump height (HB) is less than the inlet diameter (DI);
• wherein the blended wing aircraft defines a length (L) from the apex to the turbomachine inlet along the longitudinal direction and an inlet height (HI), wherein the inlet height (HI) is equal the inlet diameter (DI) minus a depth of the inlet channel at a downstream end, and wherein the bump height (HB) is greater than or equal to HI/)π×L) and less than or equal to [π×(HI+DI)]/L.