The Boeing Company

Ram Damaraju JanakiRam

Ahmed A Hassan

David B Domzalski

Bruce Dean Charles

Dino A Cerchie

Hormoz Tadghighi

An active flow control device and method for improving the aerodynamic efficiency of airfoils. The device and method pertain to the application of hybrid intermittent suction or intake of low-energy boundary layer fluid into an airfoil through one or more inlet openings while also applying intermittent blowing or expulsion of fluid out of such an airfoil into the boundary layer through one or more outlet openings for the purpose of delaying or eliminating boundary layer separation.

Method and device for altering the separation characteristics of flow over an aerodynamic surface via hybrid intermittent blowing and suction

Active flow control devices and methods are disclosed for improving the aerodynamic efficiency of airfoils. The devices and methods pertain to applying intermittent suction or intake of low-energy boundary layer fluid into airfoils in a manner delaying or eliminating boundary layer separation.

Method and device for altering the separation characteristics of air-flow over an aerodynamic surface via intermittent suction

A method and apparatus is disclosed for producing propulsion underwater with minimal acoustical emission. In basic concept, the method comprises the expulsion and sucking of liquid into and out of a liquid port of a watercraft in a manner generating compression and expansion waves adjacent the liquid port. Such expansion and compression waves generate a positive net thrust on the watercraft in a direction opposite that of their expulsion. A reciprocating member and an actuator are also disclosed for generating the forces and energy necessary to create the expansion and compression waves.

Method and device for low-noise underwater propulsion

A linear electromagnetic zero net mass jet (ZNMJ) actuator incorporating a pair of permanent magnets. The magnets are arranged such that an air gap is formed therebetween and further such that opposite poles of the magnets are arranged on opposite sides of the air gap. This concentrates the flux field across the air gap. A coil is disposed in the air gap. The coil is attached to a diaphragm which acts as a piston. When an electric current is applied to the coil, the flux field across the air gap causes a rapidly oscillating motion of the diaphragm. The actuator provides an increased rate of displacement of the piston as compared to single magnet ZNMJ actuators, and thus provides a higher momentum output across a broad frequency and voltage spectrum than conventional ZNMJ actuators using a single magnet.

Linear electromagnetic zero net mass jet actuator

An active control device for reducing blade-vortex interactions (BVI) noise generated by a rotorcraft, such as a helicopter, comprises a segmented trailing edge flap located near the tip of each of the rotorcraft's rotor blades. The various flap segments may be independently actuated according to flap deflections schedules which are tailored to address a particular operating regime with maximum efficiency and effectiveness. Through the careful azimuth-dependent independent actuation of the flap segments, blade tip vortices which are the primary source for BVI noise are (a) made weaker and (b) pushed farther away from the rotor disk (that is, larger blade-vortex separation distances are achieved), resulting in lower BVI noise.

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Mesa, AZ, United States of America

Ram Damaraju JanakiRam