The invention discloses a method and modified aerodynamic apparatuses: fluid pushers-off and fluid motion-sensors, making enable efficient implementation and use of a controllable enhanced jet-effect, either the waving jet-effect, the Coanda jet-effect, the lift-effect, the effect of thrust, the Venturi effect, and/or the de Laval jet-effect, all are controllable using the Peltier effect and/or the Seebeck effect. The modified aerodynamic apparatuses are geometrically shaped and supplied with built-in thermoelectric devices, wherein the presence of the thermoelectric devices provides for new functional properties of the modified aerodynamic apparatuses. The method solves the problem of effective control of the operation of modified aerodynamic apparatuses such as airfoil wings of a flying vehicle, convergent-divergent nozzles, loudspeakers, and detectors of acoustic waves, all of a highly-efficient functionality.

A method and apparatus are presented. An active flow control system comprises a flow control valve, a manifold, and a temperature control system. The flow control valve is configured to control a flow of air into the manifold. The manifold is operatively connected to a number of actuators. The temperature control system is configured to heat at least a portion of the flow of air.

Systems and methods according to one or more embodiments are provided for reducing noise levels in a passenger cabin of an aircraft. In one example, an aircraft includes a wing coupled to a fuselage. The wing is configured to heat air to provide a first stream of air from a central portion of a wing segment of the wing extending between the fuselage and a first engine of an aircraft. The first stream of air is at a higher temperature than an adjacent stream of air from the wing.

A method and apparatus are presented. An active flow control system comprises a flow control valve, a manifold, and a temperature control system. The flow control valve is configured to control a flow of air into the manifold. The manifold is operatively connected to a number of actuators. The temperature control system is configured to heat at least a portion of the flow of air.

A method of improving optical characteristics of an optical window operating in a flow of fluid and having first and second panes of optically transmissive materialeach having an edge adjacent to, parallel with, and at least partially coextensive with each otheris described herein. The method includes inserting a thermally conductive blade between two adjacent edges of the first and second panes of optically transmissive material; and lifting an adverse flow stagnation zone forward of the optical window by protruding the thermally conductive blade into the flow of fluid from an outer surface of the panes of the optical window.

An ice-protection system for an aerodynamic structure for an aircraft comprising: an outer skin defined by a leading edge point and a trailing edge point that are interconnected by an upper skin and a lower skin, an internal chamber defined within the outer skin configured to be in fluid communication with the atmosphere external to the outer skin via an inlet and an outlet, and at least one air heater provided within the chamber in proximity to the inlet, wherein during use, a pressure differential exists between the inlet and the outlet that causes external air to flow through the chamber from the inlet to the outlet, and wherein the heater is configured to heat the air passing through the inlet such that the temperature of the air in the chamber is sufficiently increased so as to prevent ice accretion on the outer skin.

Thermal actuation of riblets is described herein. One disclosed example apparatus includes a riblet defining an aerodynamic surface of a vehicle. The disclosed example apparatus also includes a thermal expansion element within or operatively coupled to the riblet, wherein the thermal expansion element changes shape in response to a surrounding temperature, to displace a movable portion of the riblet relative to the aerodynamic surface to alter an aerodynamic characteristic of the vehicle.

A ram air system includes a bay comprising an exterior wall defining an interior volume that at least partially encloses a ram air duct. The ram air duct includes an outlet configured to discharge an exhaust airflow at a first temperature. At least one of the exterior wall and the ram air duct defines an aperture therein providing for flow communication between the bay interior volume and the exhaust airflow such that cooling air flows from the interior volume to form a boundary layer between the exhaust airflow and the exterior wall downstream of the outlet. The boundary layer is at a second temperature that is lower than the first temperature.

Thermal actuation of riblets is described herein. One disclosed example apparatus includes a riblet defining an aerodynamic surface of a vehicle. The disclosed example apparatus also includes a thermal expansion element within or operatively coupled to the riblet, wherein the thermal expansion element changes shape in response to a surrounding temperature, to displace a movable portion of the riblet relative to the aerodynamic surface to alter an aerodynamic characteristic of the vehicle.