In accordance with embodiments disclosed herein, there are provided methods, systems, and apparatuses for predicting whether a point on a computer-generated aircraft or vehicle surface is adjacent to laminar or turbulent flow is made using a transition prediction technique. A plurality of boundary-layer properties at the point are obtained from a steady-state solution of a fluid flow in a region adjacent to the point. Included in the list of boundary-layer properties are computed coefficients or weights of mode shapes that describe the boundary-layer profiles. A plurality of instability modes are obtained, each defined by one or more mode parameters. A vector of regressor weights is obtained for the known instability growth rates in a training dataset. For each instability mode in the plurality of instability modes, a covariance vector is determined, which is the covariance of a predicted local growth rate with the known instability growth rates. Each covariance vector is used with the vector of regressor weights to determine a predicted local growth rate at the point. Based on the predicted local growth rates, an n-factor envelope at the point is determined.

Systems, equipment, and methods to deposit energy to modify and control shock waves and hypersonic or supersonic fluid flow, including systems for controlling, mitigating, and/or effecting air flow in relation to air vehicles, wind tunnels, or other assets, or the like, as well as systems, equipment, and methods for disrupting the shock structure at the inlet for the engine of an air vehicle traveling at supersonic or hypersonic speed; mitigating blast effects on vehicles; mitigating heating of throats in supersonic and hypersonic wind tunnels, as well as control the flow parameters and Mach number in their test sections.

The invention relates to a method for the numerical measurement of at least one flow-related characteristic of a profile section of a rotating profile body, around which fluid can flow, by means of a numerical flow simulation which is executed on a data-processing system and which calculates a fluid-based flow around the profile section by means of multi-dimensional computational meshes, wherein the method comprises the following steps: providing a numerical flow simulation which can be executed on a data-processing system and which is configured such that the flow velocity of the far field of the numerical flow simulation is set to zero and, instead, a lattice movement of the multi-dimensional computational mesh is performed with a translational velocity in the profile section plane, such that the relative velocity yields the incident-flow velocity of the profile section at a given angle of attack, the symmetry boundary conditions for the edges of the multi-dimensional computational mesh are set to a translationally periodic boundary condition, and the velocity component, resulting from the velocity field of the rotational movement on the edge of the profile section, in the normal direction with respect to the profile section plane are taken into consideration in the inertial terms of the balance equations of the numerical flow simulation, executing the numerical flow simulation as provided above in order to numerically measure and obtain the at least one flow-related characteristic of the profile section.

The invention relates to a device for simulating the centrifugal acceleration applied to at least one aeronautical turbomachine rotor blade. This device is notable in that it comprises at least one rotor disc (2) comprising a rim in which there are formed a plurality of pockets (23) delimited by two lateral teeth (24) and at least one simulation test (3) which comprises a screw (32), a spacer (33) and a dummy blade (31), in the said dummy blade comprises a bore (347), which is tapped over at least part of its length and in that the said dummy blade, the screw and the spacer are configured and arranged in such a way that when the screw is screwed into the tapped bore, the root (35) of the said dummy blade is engaged in the pocket in the disc, the screw comes into abutment against said spacer and presses same against the two lateral teeth situated one on each side of said pocket in the rotor disc and that this causes the dummy blade to move towards the outside of the disc.

A simple device for accurately measuring real-time air flows along a wall, and relating to a measuring device including an optical sensor configured to measure an illuminance distribution on a free surface of the optical sensor. A mobile member movably is mounted on the light sensor by partially covering its free surface, the mobile member being adapted to be freely directed by a local air flow pattern, thus, modulating the illuminance distribution on the free surface so as a current illuminance distribution measurement by the optical sensor indicates the current direction of the mobile member representing the current air flow pattern.

According to certain embodiments, a device for conditioning a flow of air includes a casing with an inlet and an outlet. The device has a flow conditioner disposed within the casing and concentrically aligned with the casing. The flow conditioner has a cylindrical portion and a domed end portion capping the cylindrical portion. The flow conditioner forms an annulus region between the flow conditioner and the casing. The flow conditioner also forms a mixing chamber interior to the flow conditioner. The flow conditioner also has a plurality of holes throughout the flow conditioner that are configured to permit air to pass from the inlet of the casing and the annulus into the mixing chamber. The device also has a flow straightener located at the outlet of the casing configured to straighten the airflow as it flows from the mixing chamber out of the device.

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.

A method and an apparatus for arranging wind turbines based on a rapid assessment fluid model and a wake model. The method for arranging wind turbines includes: calculating, via a rapid assessment fluid model and based on an anemometry data of a predetermined area in a wind farm, a flow field data of the predetermined area in the wind farm; selecting a first wind-speed area from the predetermined area in the wind farm based on at least one of an occupied area limitation, a gradient limitation, a turbulence limitation or a wind speed limitation; and calculating, via a differential evolution algorithm, coordinates for arranging wind turbines that make annual power production of each wind turbine in the first wind-speed area highest. The annual power production of each wind turbine in the first wind-speed area is calculated based on the flow field data and the wake model.

A system is provided for translating sections of an icing wind tunnel to expand a size range of water droplets. The system includes: a set of actuators coupled to a set of sections of the icing wind tunnel; and a controller coupled to the set of actuators, wherein the controller is configured to: receive data relating to a water droplet generated within the icing wind tunnel; determine a directional impact on a model within the icing wind tunnel based upon the data relating to the water droplet; and adjust at least one of the set of sections of the icing wind tunnel in at least one of an up or a down direction in a subsequent test.

Air property measurement (e.g., air temperature, air density, etc.) sensors may take the form of an all-fiber-optic device employing Rotational Raman light detection and ranging technology. Not only do the fiber optic devices described herein require no moving parts, but also these devices may be compact in design and require less power to operate as compared to conventional apparatus. As a result, embodiments may be used in applications in which physical space and power demands may be limited, such as in aircraft.