Abstract: An aircraft stores cryogenic fuel in one or more fuel tanks inside the aircraft fuselage or at other appropriate positions on the aircraft, and stores non-cryogenic fuel in plural standard jet fuel tanks e.g., inside the aircraft wings. A controller controls selective routing of non-cryogenic fuel or cryogenic (e.g., hydrogen) fuel to dual fuel engines. In one operating mode, the dual fuel engines normally use the cryogenic hydrogen fuel as the main fuel, and reserve the non-cryogenic fuel for application to the dual fuel engines only on an exception basis, thereby providing cleaner and more environmentally friendly operation.

Abstract: Propeller-driven craft (e.g., aircraft) are provided with at least one propulsion system having at least one engine and at least one aerial tractor propeller which generates a propeller propwash airflow when driven by the engine. At least one airfoil is disposed in the propeller propwash airflow of the at least one aerial tractor propeller. The airfoil is contoured and oriented relative to a swirl rotation angle (?) of the propeller propwash airflow in order to induce a forward force component on the craft in response to the propeller propwash airflow over the at least one airfoil, thus improving the craft's performance and/or reducing fuel consumption.

Abstract: Pylon fairings for an aircraft turbojet engine mounted below an aircraft wing are provided with inboard and outboard lateral faces which converge rearwardly to form a trailing edge of the pylon fairing and which are positioned so as to contact a portion of a cold flow exiting a fan duct of the turbojet engine, and a bottom face positioned above a hot exhaust flow exiting an exhaust nozzle of the turbojet engine. The trailing edge of the pylon fairing extends in an upward direction relative to an engine longitudinal axis of symmetry between a lower terminus at the bottom face and an upper terminus located at a lower surface of the aircraft wing. The lower terminus is coincident with a longitudinal midplane of the turbojet engine, and the upper terminus is offset in an inboard direction so that the trailing edge of the pylon fairing is cambered in the inboard direction between the lower terminus and the upper terminus.

Abstract: Pylon fairings for an aircraft turbojet engine mounted below an aircraft wing are provided with inboard and outboard lateral faces which converge rearwardly to form a trailing edge of the pylon fairing and which are positioned so as to contact a portion of a cold flow exiting a fan duct of the turbojet engine, and a bottom face positioned above a hot exhaust flow exiting an exhaust nozzle of the turbojet engine. The trailing edge of the pylon fairing extends in an upward direction relative to an engine longitudinal axis of symmetry between a lower terminus at the bottom face and an upper terminus located at a lower surface of the aircraft wing. The lower terminus is coincident with a longitudinal midplane of the turbojet engine, and the upper terminus is offset in an inboard direction so that the trailing edge of the pylon fairing is cambered in the inboard direction between the lower terminus and the upper terminus.

Abstract: Propeller-driven craft (e.g., aircraft) are provided with at least one propulsion system having at least one engine and at least one aerial tractor propeller which generates a propeller propwash airflow when driven by the engine. At least one airfoil is disposed in the propeller propwash airflow of the at least one aerial tractor propeller. The airfoil is contoured and oriented relative to a swirl rotation angle (?) of the propeller propwash airflow in order to induce a forward force component on the craft in response to the propeller propwash airflow over the at least one airfoil, thus improving the craft's performance and/or reducing fuel consumption.

Abstract: Aircraft air scoop icing protection systems and methods include an air duct having air inlet and outlet openings and a fairing which covers the air duct and defines an interior fairing space in which at least a forward portion of the air duct is positioned. The fairing has a forward end which surrounds the air inlet of the air duct. At least one tube is provided having an inlet end in communication with a heated air chamber associated with an airframe structure of the aircraft, and an outlet end in communication with the interior fairing space. Heated air in the heated chamber is directed through the tube to the interior fairing space so as to provide icing protection to the air duct. The air scoop icing protection systems may advantageously be employed so as to provide icing protection to air scoops associated with an aircraft engine nacelle using the residual heat from the nacelle's inlet lip primary bleed air system.

Abstract: Aircraft air scoop icing protection systems and methods include an air duct having air inlet and outlet openings and a fairing which covers the air duct and defines an interior fairing space in which at least a forward portion of the air duct is positioned. The fairing has a forward end which surrounds the air inlet of the air duct. At least one tube is provided having an inlet end in communication with a heated air chamber associated with an airframe structure of the aircraft, and an outlet end in communication with the interior fairing space. Heated air in the heated chamber is directed through the tube to the interior fairing space so as to provide icing protection to the air duct. The air scoop icing protection systems may advantageously be employed so as to provide icing protection to air scoops associated with an aircraft engine nacelle using the residual heat from the nacelle's inlet lip primary bleed air system.