Abstract: A method and apparatus for controlling the direction of the thrust vector of the engine exhaust stream in an upper surface blowing type aircraft includes ducts in the aircraft wings having rotary control valves for controlling the flow of air through the ducts from a source of high pressure to the low pressure upper surface of the wing. Introduction of the airflow at the upper surface rearwardly of the jet engine produces separation of Coanda effect attachment of the engine exhaust stream from the curved upper wing surface. Coanda effect attachment deflects the exhaust stream over the wing and toward the ground and results in a predominantly vertical thrust vector which augments lift of the aircraft. However, separation of the exhaust stream from the upper surface results in a predominantly horizontal thrust vector which augments forward acceleration of the aircraft. The fluidic action of the valves can rapidly change the thrust vector between basically horizontal and highly inclined orientations.

Abstract: A fluidic jet control apparatus, for use in a gust tunnel test system, having a fluidic nozzle with elongated blocks positioned adjacent the nozzle exit port. A rotating control valve is positioned in each of the elongated blocks. The rotating control valves have elongated passages therethrough. Elongated attachment plates are positioned forward of the exit port on opposite sides of the exit port. The blocks have elongated slots therein for admitting ambient pressure to the stream adjacent the exit port when the passages in the rotary valves are aligned with the slots. The rotary valve passages are rotated by a chain drive and sprocket wheels, driven by an electric motor to open the passages on opposite sides of the exit port 180 degrees out of phase. The rotary valves can be made with various configurations to provide various programmed disturbances in the wind tunnel.

Abstract: An oscillating liquid nozzle, for use in producing foam for fires, having a fluidic oscillating device attached to the nozzle exit with a pair of inner wall members spaced from the nozzle exit to form control ports. Outer wall members connect to the nozzle body and have scoop members positioned at their forward end which extend into the flow forward of the inner wall members to return a portion of the flow to the control ports and cause oscillation of the liquid stream leaving the nozzle exit.

Abstract: An ejector wing, for an aircraft, having inlet and diffuser doors which move from an open take-off configuration to a closed forward flight configuration and having hypermixing nozzles and root nozzles for supplying primary air into a plurality of channels in the wing structure. Apparatus is provided for controlling the air flow from the root nozzles in the boundary layer in the channels. A plurality of sensing ports are provided in the channels upstream of the root nozzles. The differential pressures at the sensing ports are used to divide the flow to the root nozzles on opposite sides of the channels.

Abstract: A vortex generator including a heat source in the base of a cylindrical member with a circular ringwing in the shape of an airfoil which is lifted upward and then impulsively released to move rapidly downward and thus generate a vortex behind it. The vorticity in the core of the vortex is highly concentrated and moves rapidly upward through cloud cover. A strong light in the center of the vortex will shine to great heights making it especially useful as an airport beacon or the like. When the invention is used with a chimney, the effluents therein are caused to proceed rapidly upward through atmospheric obstacles such as thermal inversions which have been cleared by the action of the vortex.