Abstract: The disclosed playback devices, media playback systems, and/or methods improve upon the media playback experience by selectively reducing audio quality under certain conditions. The reduction of audio quality may be based on one or more aspects of the acoustic environment, such as the number and locations of one or more users, noise levels, playback device locations relative to the acoustic environment, etc. The media playback system may monitor or periodically poll each of one or more playback devices and other devices or sensors in and around an acoustic environment to determine whether there are opportunities to reduce audio quality for one or more playback devices. This reduction in quality allows the media playback system to conserve resources in one or more aspects and, potentially, divert those resources to other aspects for purposes.

Abstract: Embodiments are described for treating a fluid, e.g., a biological fluid. The embodiments may include systems, apparatuses, and methods. Embodiments may provide for a flow cell, with a plurality of manipulation elements, through which a fluid is flowed. The fluid may be treated (e.g., exposed to energy) as it moves through the flow cell. In embodiments, the flow cell may be used to inactivate pathogens in the fluid.

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.