A propulsion system coupled to a vehicle. The system includes an ejector having an outlet structure out of which propulsive fluid flows at a predetermined adjustable velocity. A control surface having a leading edge is located directly downstream of the outlet structure such that propulsive fluid from the ejector flows over the control surface.

An end seal device for a high-lift device on an airfoil leading edge of an airfoil includes an end seal body configured to be coupled to the airfoil and having a seal body spanwise portion and a seal end. The end seal body is configured to be in a seal extended position when the high-lift device is in a device extended position. The seal body spanwise portion is disposed adjacent to the aircraft body or the airfoil leading edge and the seal end is disposed adjacent to a device end of the high-lift device when the end seal body is in the seal extended position and the high-lift device is in the device extended position. The end seal body in the seal extended position fills a discontinuity otherwise occurring between the device end and the aircraft body or airfoil leading edge if the end seal body were omitted.

An element comprising a non-stick surface for substantially cleanly removing a product which is arranged against said non-stick surface. The element comprises a first layer of an pervious material, which is configured to allow a fluid to flow there through. An outer surface of said first layer provides the non-stick surface. The element comprises a second layer of an impervious material, which is configured to substantially block a flow of fluid there through. The second layer is arranged at a side of said first layer opposite to the outer surface. The element comprises ducts or chambers which are arranged in said first layer or in between said first and second layer. Said ducts or chambers are arranged in fluid connection with said pervious material and are configured for feeding a pressurized fluid to the pervious material. At least the first layer is formed using a three-dimensional printing tool.

A system for controlling turbulence of fluid flowing past a window includes an imaging device compartment defining an interior and an exterior separated by a window, wherein the window encloses at least a portion of the interior, wherein the exterior includes at least one turbulator on a side upstream of the window positioned to induce turbulence over the entirety of a boundary layer of the fluid flowing past the window for even heat transfer between the fluid and the window.

The present disclosure is directed towards electro-fluid transducers that may influence the flow of a fluid in and around a channel. In one such embodiment, a system comprises a first electrode at least partially encapsulated by a first dielectric; a second electrode at least partially encapsulated by a second dielectric, wherein a portion of a channel exists between the first dielectric and the second dielectric; a third electrode positioned in the channel; and a fourth electrode positioned in the channel, wherein the electrodes influence a flow of a fluid in the channel upon the electrodes being energized.

A longitudinally tapered wheel spoke having a thin aerodynamic cross-sectional profile proximate to the wheel rim and tapering to a round profile toward the central hub, with the tapered section optimized to minimize drag against a combined headwind and crosswind impinging upon the primary vehicle-drag-inducing uppermost region of the wheel assembly.

A method of supersonic thrust generation includes generating a thrust supersonic exhaust plume having a first average velocity from an engine, and expelling a bypass exhaust plume having a second average velocity from the engine, the first average velocity greater than the second average velocity, so that the bypass exhaust plume inhibits coalescence of an engine exhaust plume compression shockwave.

A method of supersonic thrust generation includes generating a thrust supersonic exhaust plume having a first average velocity from an engine, and expelling a bypass exhaust plume having a second average velocity from the engine, the first average velocity greater than the second average velocity, so that the bypass exhaust plume inhibits coalescence of an engine exhaust plume compression shockwave.

A flying machine includes: a flying machine body that includes a rotor blade; a protective member that forms a frame shape inside which the rotor blade is disposed, that is rotatably fixed to both end portions of the flying machine body, and that is pipe shaped; and a connecting wire that passes through an inner portion of the protective member to connect the flying machine body and an external device together.

This disclosure relates to a method and resulting apparatus of applying a riblet sheet comprising a riblet film layer and a riblet liner layer on an airfoil surface. The method comprises applying the riblet film layer of the riblet sheet over the airfoil surface, peeling back at least a portion of the riblet liner layer from the riblet film layer to expose a portion of the riblet film layer, applying a attaching hardware or a non-textured surface film over at least a portion the riblet film layer portion; and applying the peeled back portion of the riblet liner layer over a portion of the attaching hardware.