Abstract: Provided herein is a gasifier, preferably a fixed bed, slagging, updraft oxygen gasification reactor or gasifier with features to facilitate gasification of heterogeneous waste streams producing a syngas with minimal level of condensable tars whilst simultaneously removing molten slag from the bottom of the bed via a cooled slag collector (“CSC”); syngas and other compositions produced therefrom; and processes including it.

Abstract: A lance for injecting reactants into a gasification zone of a gasifier includes a face, an outer shell, and a primary cooling circuit comprising an inlet nozzle and outlet nozzle, wherein the lance is an actively cooled lance.

Abstract: Disclosed herein are designer extracellular vesicles (EVs) that target Schwann cells (SCs). For example, in some embodiments, the EVs are decorated with HRG1/2, NRG1, or a combination thereof. These EVs can in some embodiments, be used to deliver diagnostic and/or therapeutic cargo to Schwann cells in a subject in need thereof.

Abstract: An aircraft wing comprises a leading-edge slat, the slat including a main body portion and a slat extension arranged at a spanwise end of the main body portion. The cross-sectional area of the slat extension is less than the cross-sectional area of the main body portion. The slat extension may therefore provide some of the aerodynamic benefits of the slat, while enabling the volume of the leading-edge of the wing on which the slat is mounted, to be relatively large. The chord and thickness to chord ratio of the slat extension may be less than the equivalent dimensions on the slat.

Abstract: A leading edge section of an aircraft wing comprises a main wing body portion, a droop nose high-lift device mounted adjacent to the fore region of the main wing body portion, and a door. The droop nose high-lift device is moveable between a stowed position and a first deployed position. When the droop nose high-lift device is in the first deployed position and the door is in an open position, an air flow region is exposed such that, during use, air flows through the air flow region from the lower surface to the wing upper surface of the wing. The door is also arranged to be moved during flight to control the amount of airflow through said air flow region.

Abstract: An aircraft comprises a wing (2) defining an aerofoil surface, the wing (2) comprising a drooped leading edge flap (1) being moveable between a stowed position and a deployed position. The wing (2) is so arranged that during flight when the high-lift device is in the deployed position, air may flow through an opening (7) in the wing (2) and over the aerofoil surface. During flight, air preferably flows into the boundary layer (13) on the upper surface of the wing (2). This energises the boundary layer (13), aft of the trailing edge of the drooped leading edge flap increasing its stability allowing the maximum achievable lift coefficient to be increased and hence reducing aircraft take-off and approach speeds.

Abstract: An aircraft wing comprises a leading-edge slat, the slat including a main body portion and a slat extension arranged at a spanwise end of the main body portion. The cross-sectional area of the slat extension is less than the cross-sectional area of the main body portion. The slat extension may therefore provide some of the aerodynamic benefits of the slat, whilst enabling the volume of the leading-edge of the wing on which the slat is mounted, to be relatively large. The chord and thickness to chord ratio of the slat extension may be less than the equivalent dimensions on the slat.

Abstract: An aircraft comprises a wing (2) defining an aerofoil surface, the wing (2) comprising a drooped leading edge flap (1) being moveable between a stowed position and a deployed position. The wing (2) is so arranged that during flight when the high-lift device is in the deployed position, air may flow through an opening (7) in the wing (2) and over the aerofoil surface. During flight, air preferably flows into the boundary layer (13) on the upper surface of the wing (2). This energises the boundary layer (13), aft of the trailing edge of the drooped leading edge flap increasing its stability allowing the maximum achievable lift coefficient to be increased and hence reducing aircraft take-off and approach speeds.