The present disclosure relates to shear sensor arrays. In particular, the present disclosure relates to a floating element shear stress sensor array on a chip that is calibrated to high shear levels and is calibrated to determine the sensitivity to streamwise pressure gradients.

Apparatus and methods described herein provide for boundary layer flow sensor and corresponding determination of the flow characteristics of an ambient airflow over an aerodynamic surface. According to one aspect of the disclosure provided herein, the boundary layer flow sensor includes a body configured for mounting within or below the aerodynamic surface, a pressure port configurable between an open state for taking pressure measurements within the boundary layer of the ambient airflow and a closed state that protects the pressure port from contaminants when not in use.

A pressure sensor assembly for simultaneously providing a time-resolved total pressure measurement and steady state flow angles of an airflow. The assembly includes an outer shroud having a front face, a rear face and a central bore having a wall. A dynamic absolute pressure sensor is positioned within the bore and provides a time-resolved total airflow pressure measurement. First and second spaced apart static pressure ports extend from the front face of the shroud to the rear face of the shroud and adjacent to the bore. The pressure ports provide a pressure that can be measured by pressure probes, where a combination of the time-resolved total pressure measurement and pressure measurements from the probes provides a steady state flow angle of the airflow.

A hot-humid climatic wind tunnel and a multi-field coupling control system therefor. A fan (18), a variable temperature device, a variable humidity device, a salt fog generator (8), a sky background radiation board (11), a solar radiation lamp array (12) and a rain generator (13) are mounted in a wind tunnel body (29). A wind speed sensor, a temperature sensor, a humidity sensor, a salt fog concentration sensor, a background radiation temperature sensor, a hemispherical radiometer and a rain gauge are mounted in a test section; the sky background radiation board (11) is mounted on the top of the test section of the wind tunnel, and the solar radiation lamp array (12) and the rain generator (13) are mounted on the sky background radiation board (11); the sky background radiation board (11) comprises heat conduction boards (11-2), stainless steel boards (11-3) and copper tubes (11-1); and the plurality of heat conduction boards (11-2) are divided into multiple rows and mounted on the stainless steel boards (11-3), and the copper tubes (11-1) are laid on each row of heat conduction boards (11-2). The copper tubes (11-1) are connected to an external cold and hot water device. The present invention can achieve simulation of fields of seven parameters, i.e. wind speed, temperature, humidity, solar radiation illuminance, sky effective temperature, rainfall, and salt fog in outdoor natural climate.

A transportable wind tunnel testing automobiles, motorcycles, bicycles, scale-model aircraft, building structures, and other products requiring high-quality and low noise directed air flow. The wind tunnel comprises one or more containers which can be separately transported on trailers. Each wind tunnel container comprises one or more fans, conditioning screens, acoustic baffles, and a reduction or contraction section. Wind tunnels may be connected end-to-end or side-to-side, with joined outflow. The wind tunnel containers can be used on the trailers, or can be removed and temporarily installed at a location.

A device measures at least a first physical quantity of fluid flow in a three-dimensional space having at least one predetermined interface, between at least two media. The device comprises a computer prescribing first and second conditions at the different boundaries concerning the first physical quantity, associated respectively with a first source and a second source, different to one another, the first and second sources being point sources of mass flow of fluid and/or of force. The computer calculates, by distributed point source calculation, a first value of the first physical quantity from the first condition and from the first source and a second value of the first physical quantity from the second condition and from the second source, at at least one second point, different from the first test point, then combines the values to calculate for the first physical quantity respectively from the different boundary conditions and sources.

Apparatus and methods described herein provide for boundary layer flow sensor and corresponding determination of the flow characteristics of an ambient airflow over an aerodynamic surface. According to one aspect of the disclosure provided herein, the boundary layer flow sensor includes a body configured for mounting within or below the aerodynamic surface, a pressure port configurable between an open state for taking pressure measurements within the boundary layer of the ambient airflow and a closed state that protects the pressure port from contaminants when not in use.

A structural health monitoring system includes a signal transmission element and a sensor unit. The sensor unit is designed to feed a first signal into the signal transmission element and to read out a second signal from the signal transmission element. The signal transmission element has carbon nanotubes.

An annular air flow passage, particularly for a turbine engine, comprising two radially internal and external annular walls. A measuring element is elongated in a direction between the internal and external annular walls, and a first of the internal or external ends of the element is fixed rigidly to a first of the internal or external walls. The element includes at least one tubular cavity extending along the element and supplied with pressurized fluid.

The present invention relates to a device for measuring aerodynamic magnitudes (1) intended to be placed transversally in a flow passage (12, 13) of a turbine engine comprising: an upstream body (2) having a profile of general cylindrical shape defining a leading edge (5) a plurality of sensors (4), the instrumentation lines (45) of the sensors being placed in the body (2), the sensitive elements (41) of the sensors extending at the leading edge (5); a downstream fairing (3) mounted on the upstream body (2) and defining a trailing edge (6); the downstream fairing (3) comprising, in the longitudinal direction of the upstream body (2), several sections (35) fixed independently of each other to the body (2), two successive sections (35) being connected by a flexible junction (37).