Various examples are provided related to improvements in generalized flow profile production. In one example, a method includes determining a downstream flow profile including a pressure profile and a velocity profile; fabricating a pressure profile generator including distortion screen(s) disposed on a backing structure; fabricating a velocity profile generator including turning vanes in a flow path through the velocity profile generator that are configured to generate the velocity profile; attaching the pressure profile generator to an input side of the velocity profile generator; and installing the flow conditioning device in the flow field of interest. Flow through the flow conditioning device produces the downstream flow profile in the flow field of interest. In another example, a flow conditioning device includes a pressure profile generator with distortion screen(s) disposed on a backing structure; and a velocity profile generator with turning vanes attached to an input side of the velocity profile generator.

A measurement device includes a substrate having accommodations with an emerging opening in which sensors are provided, the substrate including a cavity with a flexible printed circuit. The device is installed on a surface to characterize a fluid flow at this surface. The circuit uses hierarchized buses comprising two data communication buses emerging at the two longitudinal ends of the substrate and an internal data acquisition bus, the bus linking control circuits, each control circuit being connected to one of the communication buses, the sensors being connected to the bus in a distributed fashion on either side of each control circuit. The data from the sensors can be transmitted to the two surrounding circuits and may be acquired if one of them is faulty.

Described herein are a viscous drag reduction apparatus and a method. The apparatus includes a pair of rollers connected to a supporting surface on a roof of the vehicle, a belt having a frictional surface and partially wrapped around the pair of rollers, such that the pair of rollers allow the belt to rotate in response to an air flow generated around the vehicle when the vehicle is in motion, the pair of rollers having a length in an axial direction that is at least as long as a width of the belt, an assembly of the pair of rollers and the belt being at least partially recessed with respect to a top line of the roof, and a reverse flow cover connected to the front end of the roof of the vehicle to block an air back flow generated by the belt when rotating.

The electronic device includes an acquisition board including at least one pressure sensor and extending over a length of a sleeve of the measuring rake, a processing unit detachably electrically connected to the acquisition board and detachably fixed to the sleeve, a loading/charging unit configured to be electrically connected to the processing unit and to recharge a power supply module of the processing unit when the processing unit is electrically disconnected from the acquisition board; the processing unit including a storage module configured to store the data; the loading/charging unit allowing data to be loaded into a user device. It is thus possible to remove the processing unit in order to load the data without having to completely dismantle the measuring rack.

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).

A system reproduces aerodynamic boundary layer transition conditions in a wind tunnel test environment under ambient to cryogenic temperature conditions. The system includes a test component disposed in the test environment that defines an exterior surface. A trip dot is mounted on the test component and has a first state, in which a distal surface of the trip dot is at a first elevation relative to the exterior surface of the test component, and a second state, in which the distal surface of the trip dot is at a second elevation relative to the exterior surface of the test component. An actuator is operably coupled to the trip dot and configured to transition the trip dot between first and second states. A controller remotely causes the actuator to transition the trip dot between the first and second states.

An air-data probe system measures at least one component of freestream velocity by tracking the motion of a laser-induced breakdown (LIB) spark created in a freestream flow. Neutral density filters are positioned or deployed so that the brightness of the initial LIB spark doesn't over saturate the LIB sensor system. This allows for more consistent tracking of the LIB spark throughout the duration of the LIB spark, including the later stages where the LIB spark is not nearly as bright as the initial LIB spark, thereby allowing all or substantially all of the light generated by the LIB spark to reach the sensors. This provides for enhanced visibility and more accurate detection of the LIB spark over time and as air density changes.

An apparatus for a unique wind tunnel useable for testing various aerospace specific sensors and probes is presented. The wind tunnel apparatus as presented utilizes an effective variable nozzle and thus allows for the testing of such aerospace devices over a near infinite Mach and Reynolds numbers in subsonic flow. The variable nozzle allows for quick and easy adjustment over a minimum 1107 range of Reynolds number conditions from flow velocity of Mach 0.01 to 0.99. The optimal design of the wind tunnel also allows for adaptation to different size test tunnels, using existing facilities to reduce cost, thus enabling various aerospace design applications. The apparatus of the present invention, the variable nozzle test wind tunnel, provides a highly variable test environment in order to improve the development of advanced aerospace sensors, including benefits such as: development of flow sensors to prevent compressor stall; development of optical sensors to optimize turbine and compressor airflow; and, development of temperature sensors to increase efficiency of turbine engine operation.

Disclosed is a drag testing apparatus with variable flow field curvature and jet angle, comprising a main flow field supply device, a main flow field flow control device, a biomimetic circular test hose, a main flow field curvature adjustment device, a jet supply device, a jet flow control device, a multi-directional jet angle adjustment device, a pipe telescoping device, and a drag testing device. A liquid outlet of the main flow field supply device may be connected to a liquid inlet of the main flow field flow control device, a liquid outlet of the main flow field flow control device may be connected to a liquid inlet of the biomimetic circular test hose, a liquid outlet of the biomimetic circular test hose may be connected to a liquid inlet of the pipe telescoping device, and a liquid outlet of the pipe telescoping device may be connected to a water tank.

An air flow sensor is provided with an opening facing downstream and having a thin downstream facing edge to prevent condensation or buildup of moisture thereon. The sensor has been found to reduce entrainment of particles in a mixed phase stream. The sensor is suitable for mounting to an aircraft, and to determining air temperature and relative humidity.