Abstract: An embodiment of the present disclosure provides an airfoil comprising a trailing edge, a first fluidic outlet, and a first fluid supply. The trailing edge can have a first surface and a second surface opposing the first surface. The first fluidic outlet can be positioned on one of the first or second surfaces. The first fluid supply can be configured to eject a fluid out of the first fluidic outlet to alter an aerodynamic load experienced by the airfoil.

Abstract: An inlet flow distortion control system employs a plurality of flow control devices forming at least one array integrated into an internal surface of the inlet. The at least one array extends over an azimuthal range relative to a normal flow axis of the inlet and has a plurality of circumferential rows spaced at increasing distance from a highlight of the inlet. A control system is operably connected to the flow control devices and adapted to activate flow control devices in selected subarrays of the array responsive to a predetermined flight condition.

Abstract: Low Reynolds number forced convection heat transport within the fin channels enhanced by deliberate formation of unsteady, small-scale vortical motions using elastically fluttering thin-film reeds. The vortical motions substantially increase the local heat transfer coefficient at the channel walls and mixing between the wall thermal boundary layers and the cooler core flow. The flow mechanisms associated with production, advection and dissipation of these small-scale motions are investigated in a modular, high aspect ratio channel using micro-PIV, video imaging of the reed motion, and hot-wire anemometry. The global heat transfer enhancement in a modular heat sink prototype shows that the reed-induced small scale motions increase the turbulent kinetic energy of the flow even when the base flow undergoes transition to turbulence, leading to an increase in the local and global Nusselt number that is sustained at higher Re and a minor relative increase in losses.

Abstract: An embodiment of the present disclosure provides an airfoil comprising a trailing edge, a first fluidic outlet, and a first fluid supply. The trailing edge can have a first surface and a second surface opposing the first surface. The first fluidic outlet can be positioned on one of the first or second surfaces. The first fluid supply can be configured to eject a fluid out of the first fluidic outlet to alter an aerodynamic load experienced by the airfoil.

Abstract: An inlet flow distortion control system employs a plurality of flow control devices forming at least one array integrated into an internal surface of the inlet. The at least one array extends over an azimuthal range relative to a normal flow axis of the inlet and has a plurality of circumferential rows spaced at increasing distance from a highlight of the inlet. A control system is operably connected to the flow control devices and adapted to activate flow control devices in selected subarrays of the array responsive to a predetermined flight condition.

Abstract: A system and method for regulating and actuating bleed over a structure exposed in a fluid motion are disclosed. The bleed inlet and outlet are formed on the surface of the structure establishing fluidic communication across surfaces. The disclosed system and method contemplates active control and regulation of the bleed to modify crossflow properties such as, aerodynamic forces, hydrodynamic forces, vorticity, and moments.

Abstract: The disclosed technology includes techniques for improving efficiency of heat transfer devices, specifically condensers. An exemplary embodiment provides a device for condensing vapor bubbles comprising a quantity of liquid, a vapor source, and an acoustic transducer. The vapor source can be configured to introduce a plurality of vapor bubbles in the quantity of liquid. The acoustic transducer can be configured to provide acoustic energy to the quantity of liquid such that at least a portion of the acoustic energy is transferred to the plurality of vapor bubbles causing at least a portion of the plurality of vapor bubbles to condense in the quantity of liquid.

Abstract: An aerodynamic surface assembly is provided to facilitate control of the flow over the aerodynamic surface. The aerodynamic surface assembly includes an aerodynamic surface defining an outer mold line over which a fluid is to flow in a downstream direction. The outer mold line defines a smooth contour that is interrupted by step down region that is inset relative to the smooth contour defined by the outer mold line upstream thereof. The aerodynamic surface defines an orifice opening in to the step down region. The aerodynamic surface assembly may also include an overhang extending from the outer mold line of the aerodynamic surface upstream at the orifice. The overhang extends in the downstream direction and at least partially over the orifice. The aerodynamic surface assembly may also include a fluidic actuator defining a pair of curved passageways extending from an input region and are in fluid communication with the orifice.

Abstract: Various examples are provided for power generation using buoyancy-induced vortices. In one example, among others, a vortex generation system includes an array of hybrid vanes comprising a first vane section in a surface momentum boundary layer and a second vane section above the first vane section. The first vane section is configured to impart a first angular momentum on the preheated air in the surface momentum boundary layer and the second vane section is configured to impart a second angular momentum on preheated air drawn through the second vane section. In another embodiment, a method for power extraction from a buoyancy-induced vortex includes imparting angular momentum to preheated boundary layer air entrained by a thermal plume to form a stationary columnar vortex. The angular momentum can be imparted to the preheated boundary layer air at a plurality of angles by an array of hybrid vanes distributed about the thermal plume.

Abstract: The disclosed technology includes techniques for improving efficiency of heat transfer devices, specifically condensers. An exemplary embodiment provides a device for condensing vapor bubbles comprising a quantity of liquid, a vapor source, and an acoustic transducer. The vapor source can be configured to introduce a plurality of vapor bubbles in the quantity of liquid. The acoustic transducer can be configured to provide acoustic energy to the quantity of liquid such that at least a portion of the acoustic energy is transferred to the plurality of vapor bubbles causing at least a portion of the plurality of vapor bubbles to condense in the quantity of liquid.

Abstract: An aerodynamic surface assembly is provided to facilitate control of the flow over the aerodynamic surface. The aerodynamic surface assembly includes an aerodynamic surface defining an outer mold line over which a fluid is to flow in a downstream direction. The outer mold line defines a smooth contour that is interrupted by step down region that is inset relative to the smooth contour defined by the outer mold line upstream thereof. The aerodynamic surface defines an orifice opening in to the step down region. The aerodynamic surface assembly may also include an overhang extending from the outer mold line of the aerodynamic surface upstream at the orifice. The overhang extends in the downstream direction and at least partially over the orifice. The aerodynamic surface assembly may also include a fluidic actuator defining a pair of curved passageways extending from an input region and are in fluid communication with the orifice.

Abstract: A system and method for regulating and actuating bleed over a structure exposed in a fluid motion are disclosed. The bleed inlet and outlet are formed on the surface of the structure establishing fluidic communication across surfaces. The disclosed system and method contemplates active control and regulation of the bleed to modify crossflow properties such as, aerodynamic forces, hydrodynamic forces, vorticity, and moments.

Abstract: Marine vehicle systems and methods are disclosed. The marine vehicle can be buoyancy controlled, enabling efficient, extended use of the marine vehicle. Buoyancy actuation can enable roll, pitch, and yaw of the marine vehicle, as well as translation in any direction. One or more elastic bladders can be disposed on or in the marine vehicle. The bladders can be selectively inflated and deflated to control movement of the marine vehicle.

Abstract: Various examples are provided for power generation using buoyancy-induced vortices. In one example, among others, a vortex generation system includes an array of hybrid vanes comprising a first vane section in a surface momentum boundary layer and a second vane section above the first vane section. The first vane section is configured to impart a first angular momentum on the preheated air in the surface momentum boundary layer and the second vane section is configured to impart a second angular momentum on preheated air drawn through the second vane section. In another embodiment, a method for power extraction from a buoyancy-induced vortex includes imparting angular momentum to preheated boundary layer air entrained by a thermal plume to form a stationary columnar vortex. The angular momentum can be imparted to the preheated boundary layer air at a plurality of angles by an array of hybrid vanes distributed about the thermal plume.

Abstract: Various systems and methods are provided for power generation using buoyancy-induced vortices. In one embodiment, among others, a vortex generation system includes a nucleating obstruction; an array of vanes distributed about the nucleating obstruction, the array of vanes configured to impart an angular momentum on air drawn through the array of vanes to form a columnar vortex over the nucleating obstruction; and a set of turbine blades positioned over the nucleating obstruction, the set of turbine blades configured to extract power from the columnar vortex. In another embodiment, a method for power extraction from a buoyancy-induced vortex includes establishing a thermal plume; imparting angular momentum to boundary layer air entrained by the thermal plume to form a stationary columnar vortex; and extracting power from the stationary columnar vortex through turbine blades positioned within the stationary columnar vortex.

Abstract: A device for use in combination with a fluid flow having a biologic component and subject to an adverse response to shear stress includes a surface in contact with the flow of the fluid. The surface has a longitudinal direction extending from a leading end toward a trailing end and aligned with a direction of the flow. The surface is susceptible to inducing boundary layer formation within the flow sufficient for a resulting shear stress to induce the response. The surface includes a surface feature sufficient to induce boundary layer tripping in the flow to retard growth of boundary layer formation along the length.

Abstract: A synthetic jet ejector (101) is provided herein which comprises a diaphragm (119), a first voice coil (121) disposed on a first side of the diaphragm, and a second voice coil (123) disposed on a second side of the diaphragm.

Abstract: Marine vehicle systems and methods are disclosed. The marine vehicle can be buoyancy controlled, enabling efficient, extended use of the marine vehicle. Buoyancy actuation can enable roll, pitch, and yaw of the marine vehicle, as well as translation in any direction. One or more elastic bladders can be disposed on or in the marine vehicle. The bladders can be selectively inflated and deflated to control movement of the marine vehicle.

Abstract: A method for constructing a thermal management system is provided herein. In accordance with the method, a fan (405) is provided which is adapted to provide a global flow of fluid through the device. A synthetic jet ejector (409) is also provided which is adapted to augment the global flow of fluid over the surfaces of a heat sink (403). The ratio of the flow per unit time of the synthetic jet ejector to the flow per unit time of the fan is selected so as to achieve a desired level of heat dissipation.

Abstract: The present invention is directed to devices and methods in which one or more miniature synthetic jet actuators are integrated with a chemical fluidic sensor (ChemFET) to effect inhalation and exhalation of ambient gas samples and induce small scale mixing at the surface of the sensor. The fluidically integrated jet transports ambient gas or liquid into the jet/sensor assembly through integrated gas or liquid channels, impinges the sample gas or liquid on the sensing element, and finally ejects the sample gas or liquid back into the ambient gas or liquid. The response of the sensor in the presence of the active jet is compared to its response when the jet is inactive. The jet actuator directs entrained ambient gas or liquid toward the active surface of the sensor, and the impingement of sample gas or liquid onto the surface of the sensor results in faster response time. Other embodiments are also claimed and described.