Methods for optimizing Boundary Layer Control (BLC) systems and related systems (e.g. a Laminar Flow Control (LFC) system or systems, a Static Pressure Thrust (SPT) system or systems, a Boundary Layer Ingestion (BLI)/Wake Immersed Propulsion (WIP) system or systems, and/or low-dissipation BLC fluid-movement system or systems) to operate in concert with each other and a bellows air-moving system are disclosed.

An air mobility device improves propulsion due to the Coandă effect when flying so as to increase a flying range and reduces noise when flying.

A system includes a surface, an actuator, and processing circuitry. The surface includes one or more non-actuating zones and one or more actuatable zones. The actuator is configured to a flow property of a fluid that flows over the one or more actuatable zones of the surface. The processing circuitry is configured to obtain a value of a parameter of the fluid that flows over the surface, and operate the actuator to adjust the flow property of the fluid that flows over the one or more actuatable zones based on the value of the parameter of the fluid.

Systems and methods are provided for experimentally determining optimized placement and operating conditions, e.g., amplitude, phase, or frequency, of active flow control actuators by executing an optimization routine to sequentially activate varying subsets of active flow control actuators of a plurality of active flow control actuators spatially distributed within a flow field, calculating a cost function of each of the subsets of sequentially activated active flow control actuators based on respective measurements of one or more parameters, e.g., integral variables or proxies to the integral variables, within the flow field by one or more sensors, and determining an optimal subset of active flow control actuators based on the respective cost functions of each of the subsets of sequentially activated active flow control actuators.

Apparatuses and methods for controlling fluid flow over surfaces, e.g. wings, are disclosed. A system can include a surface influenced by a fluid flow moving across the surface, a vortex generator disposed proximate to the surface, the vortex generator for altering a vortex pattern within the fluid flow moving across the surface, and a controller for activating the vortex generator to alter the vortex pattern within the fluid flow moving across the surface. The vortex generator can comprise one or more fluid injectors each for injecting a fluid jet into the fluid flow driven by air pressure. The fluid injectors can be disposed along a leading edge of a strake where the strake is disposed on an engine nacelle and the surface comprises an aircraft wing surface. Activation can occur under open or closed loop control with sensors.

Embodiments described herein relate to a vertical take-off and landing aircraft, specifically an electric or hybrid electric aircraft having a plurality of ducted fans. The aircraft includes a plurality of axially oriented fans, laterally oriented fans, forward air intakes, side exit ports and rear exhaust ports. The aircraft achieves flight by capturing air in the intakes and diverting the air through the axially oriented fans or the laterally oriented fans through the channels selectively.

Embodiments described herein relate to a vertical take-off and landing aircraft, specifically an electric or hybrid electric aircraft having a plurality of ducted fans. The aircraft includes a plurality of axially oriented fans, laterally oriented fans, forward air intakes, side exit ports and rear exhaust ports. The aircraft achieves flight by capturing air in the intakes and diverting the air through the axially oriented fans or the laterally oriented fans through the channels selectively.

A ducted fan includes a fan and a cowl having a cylindrical shape and including an introduction port configured to introduce air from a first end portion side. The fan includes a compressor blade provided on an outer circumferential side and a thrust blade provided on an inner circumferential side of the compressor blade. The cowl includes a housing portion configured to accommodate the compressor blade in an interior thereof, an outlet configured to allow air flowing through the housing portion to be blown therethrough by the compressor blade, and an inlet configured to suck air blown out. The outlet is provided inwards in a radial direction of the cowl and near the introduction port of the cowl, and the inlet is provided inwards in the radial direction of the cowl and between the outlet and the compressor blade in an axial line direction.

Truncated flap support fairings with active flow control system for aircraft and related methods are disclosed herein. An example aircraft includes a wing having a fixed wing portion, a flap moveably coupled to the fixed wing portion, a flap support fairing coupled to a bottom of the flap, the flap support fairing having an aft end, and an active flow control system including a nozzle. The nozzle is to eject high velocity air in a streamwise direction from the aft end of the flap support fairing.

Truncated flap support fairings with active flow control system for aircraft and related methods are disclosed herein. An example aircraft includes a wing having a fixed wing portion, a flap moveably coupled to the fixed wing portion, a flap support fairing coupled to a bottom of the flap, the flap support fairing having an aft end, and an active flow control system including a nozzle. The nozzle is to eject high velocity air in a streamwise direction from the aft end of the flap support fairing.