An aircraft includes a wing having a longitudinal centerline axis, a leading edge, a trailing edge aft of the leading edge, a wing thickness, and a wing chord, an engine having a longitudinal axis vertically aligned with the wing chord and parallel to the longitudinal centerline axis, a pylon connecting the wing to the engine, and a fairing received over the pylon. The fairing defines a horizontal plane, a first plane perpendicular to the longitudinal axis, and a second plane perpendicular to the longitudinal axis, the second plane being aft of the first plane, the longitudinal axis defining a reference line when projected onto the horizontal plane. The fairing includes a fairing body defining an aerodynamic surface having an outboard portion and an inboard portion configured such that the first plane intersects the horizontal plane and the aerodynamic surface of the inboard portion at a first intersection point. The first intersection point is laterally displaced from the reference line by a first distance. The second plane intersects the horizontal plane and the aerodynamic surface of the inboard portion at a second intersection point. The second intersection point is laterally displaced from the reference line by a second distance. The second distance is greater than the first distance.

A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. The outer wall may define a vapor chamber and a capillary structure within the vapor chamber for circulating a working fluid in either liquid or vapor form to cool the leading edge. In addition, a thermal enhancement feature can enhance a heat transfer from the outer wall at the leading edge to the outer wall within the condenser section of the vapor chamber.

A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. The outer wall may define a vapor chamber and a capillary structure within the vapor chamber for circulating a working fluid in either liquid or vapor form to cool the leading edge. In addition, a thermal enhancement feature can enhance a heat transfer from the outer wall at the leading edge to the outer wall within the condenser section of the vapor chamber.

A leading edge assembly for a hypersonic vehicle is provided. The leading edge assembly includes an outer wall that tapers to a leading edge, the outer wall having a porous region at the leading edge; a coolant supply assembly in fluid communication with the porous region for selectively providing a flow of coolant through the porous region of the outer wall; and an insulation layer disposed between a portion of the coolant supply assembly and the outer wall, wherein the insulation layer is configured to reduce heat transfer between the coolant supply assembly and the outer wall.

An aerodynamic laminar flow structure comprises a flow body and a leading edge designed to face a flow circulating in a flow direction, the leading edge being movable and comprising a retracted position in which the edge of each of two flow surfaces of the flow body is joined respectively to an edge of each of two flow surfaces of the leading edge along a parting line having at least one portion inclined at an angle strictly less than 90° relative to the flow direction. The inclination of at least one portion of the parting line makes it possible to reduce drag and thus to retain a laminar flow over a major part of the exterior surfaces of the aerodynamic structure.

A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. The outer wall may define a vapor chamber and a capillary structure within the vapor chamber for circulating a working fluid in either liquid or vapor form to cool the leading edge. In addition, a dual-modal cooling structure can enhance heat transfer from the outer wall at the leading edge to the outer wall within the condenser section of the vapor chamber.

A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. The outer wall may define a vapor chamber and a capillary structure within the vapor chamber for circulating a working fluid in either liquid or vapor form to cool the leading edge. In addition, a dual-modal cooling structure can enhance heat transfer from the outer wall at the leading edge to the outer wall within the condenser section of the vapor chamber.

A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. The outer wall may define a vapor chamber and a capillary structure within the vapor chamber for circulating a working fluid in either liquid or vapor form to cool the leading edge. In addition, a dual-modal cooling structure can enhance heat transfer from the outer wall at the leading edge to the outer wall within the condenser section of the vapor chamber.

Methods, apparatus, systems and articles of manufacture are disclosed for overheat prevention of anti-ice systems for aircraft. An example aircraft includes a wing, a slat movably coupled to the wing, the slat having a compartment to receive heated bleed air, the slat including a panel, an opening formed in the panel, a door in the opening of the panel of the slat, an edge of the door hingeably coupled to the panel, the door movable between a closed position and an open position, and a latch coupled to the panel, the latch to hold the door in the closed position, the latch constructed of a thermally sensitive material such that when a temperature inside of the compartment reaches a threshold temperature, the latch releases the door to enable the door to move to the open position to vent the heated bleed air from the compartment.

Methods, apparatus, systems and articles of manufacture are disclosed for overheat prevention of anti-ice systems for aircraft. An example aircraft includes a wing, a slat movably coupled to the wing, the slat having a compartment to receive heated bleed air, the slat including a panel, an opening formed in the panel, a door in the opening of the panel of the slat, an edge of the door hingeably coupled to the panel, the door movable between a closed position and an open position, and a latch coupled to the panel, the latch to hold the door in the closed position, the latch constructed of a thermally sensitive material such that when a temperature inside of the compartment reaches a threshold temperature, the latch releases the door to enable the door to move to the open position to vent the heated bleed air from the compartment.